Owners of patent RU 2396649:

The invention relates to space technology, in particular to the designs of reference and calibration reflectors, and can be used to evaluate the radiation characteristics of multi-band radar equipment. The technical result is to simplify the design, increase reliability during operation and improve transportation conditions. The reflector is a frame with a reflective surface attached to it; the frame consists of load-bearing meridian rods located on the meridians of the sphere, which are composite, made of parts hingedly connected to each other. The meridian rods are hingedly attached to ring rods located on the parallels of the sphere, connected by free ends located at the poles of the sphere with the possibility of rotation, with the ends of a sliding telescopic rod. The hinge for connecting the parts of the rod contains a housing with springs in contact with the stops of the connected parts of the rod. The nodal joint connecting the meridian rod to the annular one is made in the form of a housing, inside of which springs are installed. The pole joint consists of a housing mounted at the end of a telescopic rod with loops installed radially in it, to which the free ends of the meridian rods are attached. 4 salary f-ly, 11 ill.

The invention relates to space technology, in particular to the designs of reference and calibration reflectors, and can be used to evaluate the radiation characteristics of multi-band radar equipment.

Spherical reflectors of inflatable and all-metal rigidly fixed type are known.

However, the known reflectors have disadvantages: inflatable reflectors have an unstable geometric shape, and all-metal reflectors of a rigidly fixed type have significant dimensions and weight, which does not allow their transportation to near-Earth orbits by associated launches.

One of the analogues is a drop-down reflector (patent No. 2214659, H01Q 15/16, 03/05/2001), in which the frame consists of a central unit and a force ring formed from intersecting rods hingedly connected to each other. The rods are hingedly and pairwise connected at their ends to the posts, which interact through the support petals with the central unit, which imparts movement to the rods through drives. The mesh fabric of the reflective surface is attached to the frame elements that define the profile of the working surface of the reflector.

This device belongs to large-sized all-metal structures of space reflectors, the significant size and weight of which do not allow their transportation to near-Earth orbits by associated launches.

The prototype is a spherical radiation reflector (patent No. 2185695, H01Q 15/14, 10/12/2000), which is a collapsible frame that consists of concentric internal and external pneumatic tubes connected to each other by flexible radial pneumatic tubes. On the radial and internal pneumatic tubes there are spherical pneumatic cells made of elastic material communicating with them. The design is equipped with a source of compressed gas, to which an internal pneumatic tube is connected using a hose. A reflective surface is placed along the entire perimeter of the frame using threads and loops attached to pneumatic cells and an internal pneumatic chamber.

This reflector is an inflatable type device, with the help of which it is possible to obtain spherical reflective surfaces. However, the need to use a source of compressed gas complicates the design, reduces reliability, creates inconvenience when rolling and deploying the inflatable frame, and requires additional costs for transporting the device.

The objective of creating the invention is to increase the reliability of the device, simplify the design, and improve operating and transportation conditions.

The essence of the invention lies in the fact that the drop-down spherical radiation reflector, made in the form of a metal folding frame on which the reflective surface is fixed, differs from the closest analogue in that the frame rods consist of parts hingedly connected to each other, and the meridian load-bearing rods are attached rotatably to ring rods located parallel to the sphere and connected by free ends using hinges located at the poles of the sphere - pole hinges, with the ends of a sliding telescopic tubular rod.

The hinge for connecting parts of the rod consists of a housing in which springs are installed, each of which is made in contact with the inner surface of the stop of the connected part of the rod, and the body is equipped with an elastic cover in contact with the outer surface of the stops.

The nodal hinge for fastening the meridian rod to the ring one consists of a housing in which the springs of the hinges of the connected parts of the meridian and ring rods are installed, and the springs in the body are located from the center to ensure a mutually perpendicular arrangement of the meridian and annular rods.

The pole joint consists of a housing attached to the end of a telescopic rod, in which, using axes, radial loops are installed for attaching to them the free ends of the folding meridian rods.

The reflective surface is formed by a woven metal mesh made of tungsten or steel microwire coated with gold.

Making the frame rods from folding components, the rotary connection of the meridian rods with the ring rods located on the parallels of the sphere and the ends of the sliding tubular telescopic rod located at the poles of the sphere allows the movement of the frame rods simultaneously in two planes, which leads to a significant reduction in the dimensions of the reflector in a folded state, simplifying the folding and deployment of the structure, increasing reliability during operation and improving transportation conditions, which is a technical result.

The invention is presented in the drawings, where Fig. 1 shows a general view of the device, Fig. 2 - connections of meridian and annular frame rods (type A), Fig. 3 - hinge connection of parts of the frame rod, Fig. 4 - hinge design from the spring side, Fig.5 - hinge from the side of the stops, Fig.6 - nodal hinge connecting the meridian and annular rods, Fig.7 - placement of springs in the nodal hinge, Fig.8 - pole hinge, top view, Fig.9 - pole hinge, section B -B, Fig. 10 - connection of the meridian rod with the pole joint.

Figure 11 shows the expanded, intermediate and folded states of the meridian rod during the opening process.

The proposed spherical radiation reflector is a metal folding frame with a mesh fabric attached to it. The frame consists of ring rods 1 located on the parallels of the sphere, and rods 2 located on the meridians of the sphere (bearing meridian rods). The rods 2 are formed by prestressed arcs. The rods 1 give the frame additional rigidity due to the exclusion of the movement of a number of points of the load-bearing rods 2 from their planes.

The meridian rods 2 are connected at their free ends with the help of hinges 3 located at the poles of the sphere (pole hinges) to a telescopic sliding tubular rod 4.

Rods 1, 2 are folding; each rod 1, 2 consists of tubular parts connected to each other by hinges 5 (Fig. 2).

The hinge 5 consists of springs 7 installed in the housing 10, each of which is made in contact with the surface of the stop 8 of the connected part of the rod 1, 2 (Fig. 3, 4, 5). The housing 10 is prefabricated and is equipped with a removable elastic cover 9 made of rigid spring steel. The stops 8, designed to be in contact with the inner surface of the cover 9, are also elastic, in contrast to the absolutely rigid ones in other embodiments of their use.

The meridian rods 2 are connected to the annular rods 1 using nodal hinges 6, each of which consists of a housing 18 with springs 7 installed in it (Fig. 6, 7). The springs 7 in the housing 18 are spaced apart from the center of the hinge 6 in such a way that a mutually perpendicular arrangement of the rods 1 and 2 is ensured.

The pole joint 3 consists of a housing 11 mounted on the free end of the rod 4 (Fig. 8, 9). Housing 11 is made with radially located

grooves with axes 12, on which loops 13 are installed radially to the pole of the sphere, each of which is connected rotatably to the corresponding part of the meridian rod 2 (Fig. 10). The housing 11 is equipped with a cover 14, secured with a screw 17 in the grooves of the housing 11, which protects the axles 12 from falling out.

In the folded state of the reflector structure, the links of the telescopic rod 4 are shifted to the center of the sphere until it stops - Fig. 11, which shows the expanded, intermediate and folded states of one of the meridian rods 2 during the opening process. All centers of the hinges 5 of the folding rods move along the radii of the sphere, and the centers of the pole hinges 3 - along the axis of the telescopic rod 4. Moreover, the stops 8 of the hinges 5, limiting the movement of rods 1 and 2, set their required direction in such a way that when folding rods 1, 2 a fan-shaped row of their angular position is formed with the vertices of the corners located in a checkerboard pattern, in which the hinges 5 are located (Fig. 10). Making connections with stops 8 ensures the bending rigidity of the opening rods 1 and 2, at which the natural frequency of the structural elements prevents a significant change in the shape of the reflector located in orbit when exposed to small disturbances.

The unfolding of the frame occurs due to the energy of the springs 7 of the hinges 5, straightening the folding rods 1, 2. In this case, the folding rods move in the direction from the center and in the final position form a spherical frame corresponding to the working position of the structure.

In the case of using a large-sized reflector design, in which an increase in the number of meridian rods will lead to an increase in the diameter of the pole joint 3, additional meridian rods 15, identical to rods 2, are used, whose free ends are connected not with the pole joint 3, but with additional ring rods identical to rods 2 16 rods located on the parallels of the sphere. The presence of rods 15, 16 makes it possible to eliminate the increase in the diameter of the pole joint 3 and maintain the smallest dimensions of the reflector when folded.

On rods 1, 2, 15, 16 a mesh fabric is fixed, which is a reflective surface. The mesh can be secured using arimid cords (not shown), placed together with the mesh in the grooves on rods 1, 2, 15, 16. At the end of the assembly, the covers of 14 pole hinges 3 are secured to the poles of the reflector.

The mesh (not shown) is a woven metal mesh that can be made of tungsten or steel microwire coated with gold. Metal parts, except axes and springs, used in the design of the reflector can be graphite-plastic or made of materials such as D16T alloy.

The proposed spherical reflector is characterized by operational reliability, ease of assembly and adjustment, stability of geometric shape, as well as small size and weight when folded, which allows its transportation to near-Earth orbits by associated launches.

1. An drop-down spherical radiation reflector containing a folding metal frame on which a reflective surface is fixed, characterized in that the frame consists of load-bearing meridian rods located on the meridians of the sphere, rotatably attached to folding ring rods located on the parallels of the sphere, connected rotatably by free ends with the ends of a sliding telescopic rod located at the poles of the sphere.

2. The drop-down spherical radiation reflector according to claim 1, characterized in that the meridian and annular rods are made of parts connected to each other by hinges, each of which consists of a housing in which springs are installed, each of which is made in contact with the inner surface of the stop being connected parts of the rod, and the body is equipped with an elastic cover in contact with the outer surface of the stops.

3. The drop-down spherical radiation reflector according to claim 1, characterized in that the meridian rods are attached to the folding annular rods using nodal hinges, each of which consists of a housing in which the springs of the hinges of the connected parts of the meridian and annular rod are installed, with the springs in the housing placed from the center to ensure mutually perpendicular arrangement of meridian and annular rods.

4. The drop-down spherical radiation reflector according to claim 1, characterized in that the sliding telescopic tubular rod is made with pole hinges, each of which consists of a housing attached to the end of the telescopic rod, in which loops are installed radially using axes for attaching free ends of folding meridian rods.

5. An expandable spherical radiation reflector according to claim 1, characterized in that the reflective surface is formed by a woven metal mesh made of tungsten microwire.

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Using a reflector is a very effective way to control light. Remember how Archimedes, using the copper shields of the defenders of Syracuse, burned the Roman squadron to the ground?

Reflectors collect and redirect rays coming from a light source. A modern reflector is a curved metal or glass surface, processed in accordance with its purpose. For example, smooth mirror reflectors allow efficient collection of light rays and are used in lens spotlights. For lensless devices, diffusion reflectors with a rough surface are more suitable; they provide uniform diffuse coverage.

The shape of the reflector can also be different. Thus, in lens instruments they are usually used spherical reflectors, rigidly fixed at a certain distance from the light source. When focusing, the entire block moves relative to the lens, and the light intensity remains constant.

Parabolic a reflector is an indispensable attribute of PAR lamps. Such lamps can generate beams of light of different widths, it all depends on the relative position of the light source and the focus of the parabolic reflector.

Ellipsoidal reflectors have two focuses, and if the light source is placed in one of them, the reflected rays will be collected at the second focus of the ellipse. This property of ellipsoidal reflectors is actively used in profile spotlights. By combining the secondary focus of the reflector with the focus of a plane-convex lens, a parallel luminous flux is obtained at the output.

Reflectors combined type combine two surfaces that smoothly transition into one another. One of the surfaces collects and intensifies the rays coming from the light source, and the other redirects the light flux, shifting it in the desired direction. Such reflectors are often used in cycloramic luminaires.

Reflectors are probably the most important elements in luminaire design for controlling light. Initially, glass with a mirrored back surface (mirror reflector technology) was used as a reflector. Currently, anodized aluminum, chrome, or aluminum-coated plastic are used as reflective materials.

Plastic reflectors are fairly inexpensive, but can only accommodate a limited thermal load. Therefore, they are not as durable as aluminum reflectors, whose high-strength anodized coating provides mechanical protection and can be exposed to high temperatures.

Aluminum reflectors are available in a variety of qualities, ranging from high-grade, high-purity aluminum to pure aluminum-only reflectors.

The thickness of the final anodized coating depends on the application:

• for interior spaces - about 3–5 microns;
• for use in external spaces or chemically aggressive environments - up to 10 microns.

Reflector surfaces can have a mirror or matte finish. Matte creates a brighter and more uniform light. To make the reflected beam slightly diffused, to achieve softness of light and to balance unevenness in distribution, the surface of the reflector can have a faceted or multi-plane structure.

Metal reflectors have a dichroic coating that can control the UV or IR components of the light.

The distribution of light is determined to a large extent by the shape of the reflector. Almost all reflector shapes can be classified as parabola, circle or ellipse.

Parabolic reflectors

The most widely used reflectors are those with parabolic reflectors. They allow you to control the light in various ways:

• narrow beam;
• wide beam;
• asymmetrical distribution;
• provide specific highlights.

In the case of parabolic reflectors, the light emitted by a light source placed at the focus of the parabola is emitted parallel to the parabolic axis. The more a light source deviates from an ideal point source relative to the diameter of the parabola, the more the rays of emitted light will diverge.

If the contour of the reflector is made by rotating a parabola or parabolic segment around its own axis, then the result will be a reflector with narrowly focused light distribution.

If the reflector contour is made by rotating a parabolic segment around an axis that is at an angle to the parabolic axis, then the result will be a reflector with Widely directional light distribution.

Controlling the angle of the light beam allows you to create luminaires that satisfy a wide range of light distribution and glare control applications.

Parabolic reflectors can also be used with linear or flat light sources. For example, PAR lamps or fluorescent lamps. In this case, the reflector has not so many tasks - to produce directional light, but to optimally limit the glare effect.

Such designs can be found not only in lamps. They are also used in light control systems. For example, parabolic blinds for roof windows control direct sunlight so that glare does not occur and does not disturb the owner.

Spherical reflectors

In the case of spherical reflectors, the light emitted by a lamp located at the focal point of the sphere, the light is reflected at this focal point. Spherical reflectors are used primarily as an aid in combination with parabolic reflectors or a lens system.

They direct the light stream forward onto a parabolic reflector or use the light emitted backwards, returning it back to the lamp.

Elliptical reflectors

In the case of elliptical reflectors, the light emitted by a lamp located at the first focus of the ellipse is reflected towards the second focus. The second focus of the ellipse can be an imaginary, secondary light source.

Elliptical reflectors are used in recessed ceiling lamps with the task of creating flood lighting from the ceiling down. Elliptical reflectors are also ideal when only a small hole for the fixture can be used to illuminate a fairly large area.

A second focal point located on the level can be blinding, so lighting distribution and glare can be controlled using an additional parabolic reflector.

Special reflectors

In addition to the classic parabolic, spherical and elliptical, other types of reflectors are used in the production of lamps, designed to solve certain problems.

For example, cut-off reflectors. This is a type of parabolic reflector with a shifted (variable) focal point. Used when the light source is larger than a precise point light to control the angle of reflected light.

Involute reflectors. A type of reflector that minimizes back radiation to the light source. This avoids excessive heat and reduces lamp performance. Such reflectors are often used when working with gas-discharge light sources.

We have considered only a small part of the theory of organizing light control. New articles are still to come. Subscribe to our blog and receive the latest articles directly to your email.

The patented utility model relates to space technology, namely, to spherical reflectors with a mesh surface deployed in orbit, which are a calibration artificial earth satellite (AES). According to the patented utility model, the power frame of the reflector is made in the shape of a sphere formed by meridian ribs, which are made of rod elements connected to each other by meridian hinges. To impart the necessary rigidity, the power frame of the spherical reflector contains an equatorial belt connecting the middles of the meridian ribs. The equatorial belt is made of rod elements connected to each other by equatorial hinges, and the radio-reflective surface mounted on the surface of the load-bearing frame is made of metal mesh fabric. The power frame contains from 8 to 36 meridian ribs, each meridian rib contains from 8 to 36 rod elements connected to each other by meridian hinges, the equatorial belt contains from 8 to 36 rod elements connected to each other by equatorial hinges of two types. The technical result is that the developed utility model makes it possible to significantly simplify the final structural implementation of a spherical reflector, eliminate sufficiently large structural elements, radically reduce the overall dimensions of the reflector when folded, which increases the convenience of its transportation to low-Earth orbit, and reduce the requirements for the dimensions of the transport compartment for its delivery into orbit. 7 p.f., 10 ill.

The patented utility model relates to space technology, namely, to spherical reflectors with a mesh surface deployed in orbit, which are a calibration artificial earth satellite (AES).

The developed spherical reflector can be effectively used to solve a variety of applied and scientific problems, in particular, as a reference target with a precisely known value of the effective scattering area (RCS) when testing and monitoring the functioning of radar stations (radars) with the requirements for accuracy characteristics specified for it and by energy potential, to determine with high accuracy the coordinates of space satellites in orbit, to assess the reflection characteristics of multi-band radar equipment.

It is known that the best objects for full-scale radar calibration are reflective spherical surfaces of various diameters. To effectively solve the constructive problem of creating a drop-down space reflector, the applicant analyzed numerous technical solutions in this area, varied in their final implementation.

For example, various designs of “umbrella-type” reflectors are known (US patents 2945234; 3286259; 4482900; 5446474;

5864324; 5680125;6028570).

A common characteristic disadvantage of patented solutions is their structural complexity and large overall dimensions when folded, which significantly limits the scope of their effective application.

A deployable large-sized space reflector is known (RF patent 2266592; H01Q 15/16). The invention relates to deployable large-sized reflectors of space antennas. The technical result consists in minimizing the height of the reflector in the transport position, which is achieved by making the power ring of the reflector in the form of a pantograph with telescopic stands. The disadvantage of the known design is the complexity of the design and the increased overall dimensions of the device when folded.

A deployable large-sized spacecraft reflector is also known (RF patent 2350519; H01Q 15/16).

The invention relates to space mirror antennas with a deployable umbrella-type reflector having a diameter of about 12 m or more. The reflector contains a central unit in the form of a coaxially located base and flange, as well as a load-bearing frame mechanically connected through a form-building structure to the mesh fabric. The load-bearing frame is formed from straight spokes hinged to the base, made in the form of mesh rod structures with consoles attached to their ends.

The technical result of the invention is to provide a high-precision profile of the working surface of the reflector (standard deviation from the theoretical profile is not more than 1.3 mm) after all types of tests simulating its operating conditions, as well as to simplify the design and reduce the weight of the reflector.

The characteristic disadvantage of the patented solution is the traditionally complex design and significant overall dimensions when folded.

Designs of umbrella antennas for spacecraft are also known (RF patent 2370864; H01Q 15/16; RF patent 2370865; H01Q 15/16).

The inventions relate to space technology, in particular to mirror antennas with a deployable large-sized umbrella-type reflector.

The technical result of the invention according to RF patent 2370864 is to expand the operational capabilities of the reflector. The umbrella antenna consists of a feed and a reflector, which includes a central unit, a power frame pivotally connected to it, made in the form of spokes, mechanically connected to the mesh fabric, a hub attached to the central unit on the opposite side of the reflector opening, which is in the area of ​​the free end with using guy ropes, it is connected to the knitting needles by a single center. The technical result is achieved due to the fact that at the free end of the hub there is installed a device for adjusting the shape of the radio-reflective surface of the reflector, the output elements of which are made in the form of screws and are located between a single center and each guy wire, with the ends of which they are mechanically connected with the possibility of rotational movement and independent of each other. other changes in the effective distance from the point of connection of each guy with the spoke to a single center. The longitudinal axes of these output elements mutually coincide with the corresponding axes drawn through a single center and the point of connection of the corresponding guy with the spoke.

The technical result of the invention according to RF patent 2370865 is to increase the reliability of the reflector opening. The umbrella antenna consists of a feeder and a deployable reflector, including a central unit, a power frame connected to it, made in the form of spokes, mechanically connected to the mesh through a form-building structure made in the form of cords and tie-down threads, and a mesh located on the opposite side of the mesh. opening of the reflector on the form-building structure. The technical result is achieved due to the fact that covers are put on the knitting needles, and the mesh is made in the form of screens located between two adjacent knitting needles and made of elastic thin material with low electrical conductivity. The through free cells of the screens are smaller in size compared to the minimum possible cross-sectional sizes of tie threads and cords. Each screen is glued with one radial boundary zone to the surface of the cover of a specific spoke, and with the other radial boundary zone it is connected via Velcro to the outer surface of the boundary zone of the adjacent screen.

The analysis shows that the significant design disadvantages of these devices are their bulkiness when folded and the complexity of the circuit design, which causes low operational reliability of the design when deployed in orbit.

A spherical radiation reflector is known (RF patent 2185695;

H01Q 15/14), which is closest in technical essence and design implementation to the patented utility model, and which is accepted as a prototype.

The radiation reflector described in RF patent 2185695 contains internal and external pneumatic chambers, radial struts made in the form of a flexible tube with holes, on which spherical pneumatic cells made of elastic material are built up, interacting with each other.

To form a rectangular reflector, the pneumatic system is made in the form of a matrix of mutually perpendicular flexible tubes communicating with each other with holes, around which cubic pneumatic cells are built up, interacting with each other and the mirror surface.

The reflector with a spherical surface contains radial and concentric sectional pneumatic tubes mechanically and pneumatically connected to each other. To create them, flexible tubes have holes around which pneumatic cells are built in the shape of a sector of a spherical shell. When the pneumatic cells are inflated, they form a hemispherical reflector shell with a spherical concave surface.

Strips of an electrically conductive metal coating are applied to the base of the pneumatic cells on the convex side, forming electrically conductive rings. These rings are connected to a source of adjustable voltage relative to the metal coating of the mirror surface. Under the influence of electrostatic forces, the mirror surface takes on a spherical shape.

In addition, to reveal a flat-shaped film reflector, the outer ring and radial struts can be made in the form of garlands of hollow balls (or rings) strung on cables, the ends of which are passed through the holes of the rigid inner ring and connected to a mechanism for tensioning and fixing the position of the cables.

A reflector with a spherical surface contains concentric rings in the form of a garland of radiation-reflecting cells in the shape of a sector of a spherical shell, strung on two cables passed through the middles of the opposite side faces of the cells. In this case, the concentric rings are connected to each other by radial cables, and the ends of the concentric and radial cables are connected to a mechanism for tensioning and fixing the position of the cables.

A significant disadvantage of the known spherical reflector according to RF patent 2185695 is its structural complexity and reduced reliability of the deployment process in orbit, which is due to the presence of a large number of its constituent structural elements, the presence of various types of cables and mechanisms for tensioning and fixing the position of these cables, the presence of several pneumatic chambers and their systems inflation, a significant number of dynamically used structural elements.

This utility model solves a technical problem:

Simplifying the design of a spherical reflector,

Increasing the reliability of its deployment in orbit,

Increasing the lifespan in orbit.

The solution to the stated technical problem is achieved as follows.

An drop-down spherical reflector, similar to the reflector described in RF patent 2185695, containing a power frame of hinged-rod elements on which the reflective surface is fixed, according to the patented utility model, the power frame of the reflector is made in the shape of a sphere formed by ribs-meridians, which are made of rods elements connected to each other by meridian hinges. It is provided that the meridian ribs are fixed at their ends in oppositely located pole hinges.

In accordance with the patented solution, to impart the necessary rigidity, the power frame of the spherical reflector contains an equatorial belt connecting the middles of the ribs - meridians. The equatorial belt is made of rod elements connected to each other by equatorial hinges.

The patented solution provides that the radio-reflective surface fixed on the surface of the load-bearing frame is made of metal mesh.

According to the patented utility model:

The power frame contains from 8 to 36 meridian ribs, each meridian rib contains from 8 to 36 rod elements connected to each other by meridian hinges;

The equatorial belt contains from 8 to 36 rod elements connected to each other by equatorial hinges of two types.

The power frame is made with a diameter from 1 to 12 meters.

Laser corner reflectors are fixed on the surface of the load-bearing frame.

The patented utility model provides the ability to control the results of autonomous deployment of a spherical reflector in orbit. In this case, the spherical reflector is equipped with sensors in the form of a limit switch, which are mounted on equatorial and meridional hinges, and also contains information channel equipment with its own power source for communication with the spacecraft and ensuring the transmission of command and telemetric information.

The technical result of a patented utility model is that the developed utility model allows:

Significantly simplify the final structural implementation of the spherical reflector, eliminate (inherent to the prototype) sufficiently large structural elements, and accordingly radically reduce the overall dimensions of the reflector when folded, which increases the convenience of its transportation to low-Earth orbit, reduce the requirements for the size of the transport compartment for its delivery to orbit;

Reducing (minimizing) the number of functional elements included in the final design of a spherical reflector significantly increases the reliability of deployment of the reflector in orbit and increases its operational life;

At the same time, the patented design is characterized by increased accuracy and stability of the geometric shape of a spherical reflector deployed in orbit, the radio-reflective surface of which provides high reflection characteristics, which qualitatively improves all the main operational characteristics of the spherical reflector.

The optimal overall dimensions and reduced weight of the developed reflector when folded allow it to be transported to near-Earth orbits by associated launches, which radically increases the economic efficiency of operating the patented design.

The essence of the patented utility model is explained by a description of the developed spherical reflector and graphic materials showing:

Fig.1. - Diagram of a spherical reflector in an expanded state.

Fig.2. - Meridian hinge ((a - side view, b - bottom view);

Fig.3. - Connection of the rod and the meridian hinge ((a - side view, b - bottom view);

Fig.4. - Pole joint.

Fig.5. - Equatorial hinge.

Fig.6. - Connection of rods in the rib-meridian (fragment in the open state).

Fig.7. - Folded state of the rib-meridian.

Fig.8. - Spherical reflector in folded state (view from the pole joint).

Fig.9. - Spherical reflector in folded state (section in the equatorial plane).

Fig. 10 is a block diagram of the information channel equipment with its own power supply for monitoring the results of autonomous deployment of the reflector in orbit.

When deployed, the patented reflector (Fig. 1) is a spherical shell formed by a knitted metal mesh fabric stretched over a self-expanding power frame.

The power frame of the reflector is made in the shape of a sphere and contains (Fig. 1) an oppositely located pair of pole hinges 1, meridian ribs 2, which are made of rod elements 3 connected by meridional hinges 4 (Fig. 2). To ensure folding, adjacent hinges 4 in the meridian ribs are located towards each other (Fig. 6).

All meridian ribs 2 are fixed at their ends in the corresponding pole hinges 1, located oppositely (one opposite the other).

To provide additional rigidity, the reflector's power frame contains an equatorial belt 5 connecting the middles of the meridian ribs 2.

The equatorial belt 5 is made of rod elements 6 connected to each other by equatorial hinges of two types. At the intersection of the meridians and the equator, four-finger equatorial hinges 7 are used (Fig. 5). Between the hinges 7, the rods 6 are connected by two-finger hinges 8, which are similar in design to the meridional hinges 4 (Fig. 2). To ensure folding, the hinges 8 are also installed towards the equatorial pair of hinge pins 7 (Fig.9).

The reflective surface 9, fixed on the surface of the load-bearing frame, is functionally a radio-reflective surface, formed by a knitted metal mesh, made, for example, of tungsten or steel microwire coated with gold or nickel.

When developing this reflector, it was taken into account that the number of partitions along the equator depends on the required accuracy of approximation of the surface of the sphere; the number of partitions along the meridian is equal to the number of partitions along the equator.

Research conducted by the applicant indicates that to ensure the spherical shape of the reflector and the required rigidity, the load-bearing frame:

And the equatorial belt 5 can contain from 8 to 36 rod elements 6, interconnected by equatorial hinges 7 and 8.

The patented utility model provides that the power frame can be made with a diameter of 1 to 12 meters. At the same time, in order to achieve increased accuracy of alignment of the location means, it is possible to place laser corner reflectors on the surface of the power frame (not shown in the figure).

Individual technical elements of a spherical reflector may have the following possible design implementation.

The meridian hinge 4 (Fig. 2) can be made in the form of hinges 10, a body 11, two axes 12 and two springs 13. The hinges 10 are put on the axis 12. The springs 13 are also put on the axis 12 and are located inside the loops 10. One end of the spring 13 are embedded in the body 11, the other in the hinges 10. When folded, the spring 13 is twisted and stores energy for deployment. Rod elements 3 are attached to hinges 10 (Fig. 3).

The pole joint 1 (Fig. 4) consists of a housing 14 and hinges 15 mounted on a ring axis (inside the housing, not shown). The hinges 15 attach the rod elements of 3 ribs-meridians 2.

The equatorial hinge 7 (Fig. 5) serves to connect the rod elements 3 of the meridian ribs 2 and the rod elements 6 of the equatorial belt 5. The equatorial hinge 7 consists of hinges 16, a body 17, axes 18 and springs 19. The axes 18 are fixed in the body 17, loops 16 and springs 19 on axes 18. The rod elements 3 of the ribs-meridians 2 and the rod elements 6 of the equatorial belt 5 are attached to the loops 16. When folding the reflector elements, the springs 19 also store energy for the subsequent deployment of the reflector in orbit.

A fragment of a folded edge-meridian is shown in Fig.7.

To monitor the result of autonomous deployment in orbit, the patented reflector is equipped with sensors in the form of a limit switch, which are mounted on meridional and equatorial hinges, and also contains information channel equipment with its own power source for communication with the spacecraft and ensuring the transmission of command and telemetric information.

The information channel equipment contains (Fig. 10) its own power supply 20, controller 21, cable amplifier 22, cable 23 (length up to 100 meters) connected in series.

To control autonomous deployment in orbit, the spherical reflector (Fig. 10) contains N sensors 24 of the “open contact” type and a multi-core cable 25, through which information about the state of the set of sensors 24 (closed or open) is transmitted to the controller 21.

Sensors 24 in the form of a limit switch (not shown in Figs. 1-9) are mounted on the meridional and equatorial hinges of the spherical reflector (on hinges 4 and 7 and/or 8).

To explain the principle of operation of the plurality of sensors 24, it should be explained that when the spherical reflector is in the folded state, all sensors 24 are in an open state (logical state "0"). When the spherical reflector is opened, all sensors 24 must go into a closed state and current begins to flow through the corresponding wires of the multi-core cable 25 (logical state “1”). Each sensor 24 has its own pair of wires in the multicore cable 25. If, after opening the spherical reflector, at least one of the sensors 24 does not go to the logical state “1”, this means that the corresponding pair of hinges has not fully opened, which is a signal of incomplete (incorrect) opening of the spherical reflector. The signal about this is transmitted through the controller 21, which provides sequential polling of the state of each sensor 24. Then the signal is transmitted through the cable amplifier 22 and the two-wire cable 23 to the information equipment 26 of the launch vehicle stage.

For example, a standard battery or rechargeable battery can be used as its own power source. To implement controller 21, standard circuit designs and corresponding microcircuits are known: current switches (K176KT1, K561KTZ), multiplexers (K561KP2 and KR1561KP2) and decoders (KR1561ID6, K561ID1). Cable amplifier 22 can be implemented on standard microcircuits of the type (K176KT1, K561KTZ, KR1561KTZ).

The information channel equipment with its own power source can be placed, for example, on the inside of one of the pole joints 1. The number of sensors 24 depends on the size of the spherical reflector, the number of meridian ribs 2 and the number of hinges in the design of the spherical reflector. For example, to achieve the results of autonomous deployment of a reflector in orbit, the number of sensors 24 may be equal to half the number of hinges in the reflector structure.

The applicant considers it necessary to note that specialists working in the field of electronic equipment for spacecraft have appropriate knowledge about the availability of various components for the final implementation of information channel equipment, in addition to those components that are given as possible implementation options.

The specific circuit implementation of the information channel equipment of the patented utility model and the identification of all possible initial components and components for the production of such equipment is not difficult for specialists, since it follows from the state of the art on the basis of practical data and includes well-known standard components and components fixed in various scientific and technical publications and reference books, it should also be noted that the entire element base is mass-produced and available for free purchase, due to which a more detailed disclosure of the initial components and components of the information channel equipment is impractical.

Folding of the patented spherical reflector for its transportation and placement in the transport compartment is carried out in the following sequence.

When folded, the spherical shell of the reflector is transformed into a sphere of smaller diameter. A view of the folded reflector from the side of the pole joint is shown in Fig. 8, along the equatorial section in Fig. 9.

The reflector is fixed to a special device using the pole joints. A technological compressive adjustable harness is applied to the equatorial belt (Fig. 1). All hinge elements 4 of the meridian ribs and hinges 8 of the equatorial belt are folded (Fig. 7) using a technological device, which is a meridian-ring belt structure with an adjustable length of belt rods. In this case, the reflector frame loses stability and is ready to fold. Then, sequentially, according to a certain algorithm, the lengths of the rods of the tape structure and the compression strapping are shortened until the reflector is folded to the state shown in Fig.8 and Fig.9.

The developed spherical reflector is used as follows.

The folded reflector (Fig. 8, Fig. 9) is located under the fairing of the spacecraft (SV). After insertion into orbit and release of the fairing, the reflector is separated from the spacecraft in folded form at a distance that ensures safe deployment, and is opened by the energy of the hinge springs upon command from the control point or on-board unit. The deployment control system transmits information to the control center via a telemetry channel. The opening of the spherical reflector in orbit occurs automatically due to the energy stored in the springs of the hinged elements of the frame when folded. After deployment, the reflector takes the shape of a sphere with a calibrated EPR value (Fig. 1).

The reflector can be used, for example, to calibrate the energy potential of a radar station (radar) and thereby estimate the maximum range of the radar for objects with other ESR values. To do this, after determining the spatial coordinates of the reflector, the radar emits a radio signal of a certain power in its direction and, based on the level of the received reflected signal, receives a calibration value of the radar's energy potential, taking into account the known EPR value of the reflector. Based on the energy potential of the radar obtained as a result of calibration, using the well-known radar range formula, the maximum range of the radar over objects with other ESR values ​​is estimated, which is one of the tasks of radar calibration. Further, by comparing the levels of reflected signals from other objects with the level of the signal from the reflector, it is possible to obtain the values ​​of their EPR, which in some cases is of independent interest.

When accurately measuring the spatial coordinates of the reflector, for example, using laser ranging stations operating on the reflected signals of corner reflectors mounted on a spherical reflector, it can also be used for radar alignment.

Test tests of the patented utility model carried out by the Applicant confirmed:

High performance characteristics of the spherical reflector obtained in real time;

Compactness and optimal weight of the structure when folded for transportation, high reliability of deployment of the device in orbit.

1. An drop-down spherical reflector containing a power frame of rod elements on which a reflective surface is fixed, characterized in that the power frame of the reflector is made in the shape of a sphere formed by meridian ribs, which are made of rod elements interconnected by meridional hinges, all ribs -meridians with their ends are fixed in oppositely located pole hinges, while to give additional rigidity, the load-bearing frame contains an equatorial belt connecting the middles of the meridian ribs, which is made of rod elements connected to each other by equatorial hinges, and a reflective surface fixed on the surface of the load-bearing frame , made of metal mesh fabric.

2. Drop-down spherical reflector according to claim 1, characterized in that the power frame contains from 8 to 36 meridian ribs.

3. Drop-down spherical reflector according to claim 1, characterized in that each meridian rib contains from 8 to 36 rod elements connected to each other by meridional hinges.

4. Drop-down spherical reflector according to claim 1, characterized in that the equatorial belt contains from 8 to 36 rod elements connected to each other by equatorial hinges.

5. Drop-down spherical reflector according to claim 1, characterized in that the load-bearing frame is made with a diameter of 1 to 12 m.

6. Drop-down spherical reflector according to claim 1, characterized in that laser corner reflectors are fixed to the surface of the load-bearing frame.

7. The drop-down spherical reflector according to claim 1, characterized in that to control autonomous deployment in orbit, the spherical reflector is equipped with sensors in the form of a limit switch, which are mounted on meridian and equatorial hinges, and contains information channel equipment with its own power source for communication with the space device and ensuring the transmission of command and telemetric information.

The simplest and most common accessory in studio photography is a reflector. The beautiful word “reflector” is translated as reflector. Accordingly, the essence of his work is the reflection of light.

A reflector is used to turn non-directional light into directional light. You can understand the operating methodology of reflectors from these diagrams, which have not yet been found on Russian-language photographic resources. Well... It's time to close this gap too.

I will briefly describe all the main options for reflectors so that you can further understand not only photographic reflectors, but also any others. For example, in reflectors for car headlights, lanterns, etc.

The article turned out to be relatively long because... reflectors “this is our everything.” I would recommend taking a closer look at the light output diagrams from the reflector and the comments for each reflector. For the reason that the cut-off pattern depends on the distance and size of the reflector, and the diagrams show the principle itself, with the help of which you can understand what to generally expect from the reflector by moving it.

There are no analogues of this article on photographic resources. There are only light spots, but the principle of operation of reflectors is not described anywhere. All information was gleaned from specialized sources, such as the “Carl Zeiss campus”, websites of manufacturers: car headlights; lanterns and spotlights; telescopes, websites of various universities, etc.
I would be glad if experts in the field of designing reflectors and lighting devices constructively comment on the article and maybe add or correct something. I would also be grateful for 3D modeling of light sources if anyone wants to help design the article beautifully (3Dmax, Maya, Pro/ENGINEER aka PTC Creo Elements/Pro, etc.). You can even pay a little and cooperate in the future if you are satisfied with the result.

All reflectors are kindly provided by the company Falcon Eyes.

What you need to know about reflectors

The nature of the luminous flux when using a reflector depends on:

— its geometric shape and size;
— properties of its surface;
— lamp location;
— distance to the lighting object.

Reflector operation schemes

Super-brief educational program on geometry

A ball is a volumetric circle. A sphere is the surface of a ball. If we rotate the parabola, we get an elliptical paraboloid. A circle is a special case of an ellipse. All these figures are conic sections.

Spherical reflector

The lamp is in the center of the reflector.

spherical reflector, lamp in the center

hemisphere

If you place the flash lamp in the center, the light will be reflected back into the lamp. This increases the luminous flux output by approximately 40%. But since the rays diverge quite widely, such a reflector is not very convenient to work in studio photography.

The lamp is in the focus of the reflector.

spherical reflector, lamp in focus

The sphere on which the reflector's focal point is located is defined as half the radius of the reflector. In this case, the output will be parallel rays, which is good for uniform illumination. Such a reflector is often used in flashlights in conjunction with a Fresnel lens.

The most famous and widely used spherical reflector is (beauty dish).

There is no guarantee that the lamp in your particular beauty dish is in focus. There are as many shapes, sizes and positions of beauty dish lamps as there are manufacturers. You yourself will be able to evaluate what you have knowing the principle.

Another example of a spherical reflector is a photo umbrella. It is attached to the flash with its rod and produces soft but poorly controlled light.

photographic umbrella

A photo umbrella is used due to its compactness and low cost. The photo umbrella also has the ability to move relative to the flash. The inner surface of the umbrella can be silver, gold or matte white. Silver surfaces produce a harsher light, while matte white surfaces produce a softer light.
There are also umbrellas “for light”, but this is no longer a reflector, which is discussed in this article, but a diffuser, so I will not present it here.
I’ll add more about photo umbrellas later, once I’ve taken test pictures.

Parabolic reflector

This type of reflector can also collect rays and direct them in parallel if the light source is in the focus of the reflector.

parabolic reflector with a lamp at focus

If the lamp is brought closer from the focus to the reflector, the rays will diverge, and if they are moved away from the focal point, they will converge.

paraboloid

Examples of using a parabolic reflector in studio instruments.

Let's move on to the most stunning reflector. Not by its characteristics (each tool has its own task), but by its size! Here I will call parabolic reflectors “PARA”, after the name of the most popular parabolic reflector - Broncolor PARA. Some photographers use PARA mainly to shock the client and convince them that this is a serious studio.

Areas of use: PARA is widely used in the West in location shooting, i.e. in outdoor shooting. Since it is foldable, despite its large size it can be folded quite compactly for transport by car. Its advantage is the soft light and the fact that the photographer can stand directly between the PARA and the model without practically changing the cut-off pattern (i.e. it actually blocks part of the light, but due to the size of the PARA this is not significant). PARAs come in a variety of brands from cheap (within reason) to very expensive and desirable ones.

Elliptical reflector

Special types of reflectors

In addition, there are special types of reflectors that are used for specific tasks.

Conical nozzle Falcon Eyes DPSA-CST BW

Application area The background nozzle follows from its name; it serves to illuminate the background. Thanks to its shape, it illuminates the background more softly than, for example, a standard elliptical reflector.

It didn’t turn out to be a perfectly beautiful shot (the background is a little uneven), but the essence is clear. The background nozzle distributes the light flux more evenly.

Results:

In this article I touched on only a few types of reflectors. It is clear that if we take such a comprehensive concept as “reflector”, then we can write about different types of reflectors for a long time. And in the following articles we will continue to get acquainted with different types of reflectors.

You have become acquainted with basic studio reflectors, the principles of their operation and their classic applications. The scope of application is actually limited only by your imagination and the capabilities of a particular reflector.

update
When coming to a photo studio, I recommend using slang names for reflectors. For example, if you need a large parabolic reflector, it is called PARA (“Pair”, large umbrella).
If you want a small elliptical, it's called a "standard reflector" or "pot."
A beauty dish is a beauty dish. In English, Beauty Dish (“plate for beauties” :)).
There is also a softbox, stripbox, octobox, etc. which will be discussed in the following articles because These are no longer just reflectors, but separate devices.

I will be glad to hear your comments and see examples of your work with various reflectors.

There will be a new article on studio accessories coming soon! Stay in touch:)

Let's let the girl go... let her float...

shot using a beauty dish in cloudy weather