Fixture to mount assembly units at article. RU patent 2510606.
 Device for jointing two curved frames of aircraft or spacecraft / 2507112Invention relates to aerospace engineering. Proposed joint comprises connection element and connection sections of two curved frames of the craft. Note here that said connection element can be attached by predefined connection sections to appropriate connection sections of two frames. Said joint differs from known designs in that said predefined connection elements feature straight shape while at least appropriate connection sections of two frames have straight section of inner girths for straight attachment of predefined connection sections of connection element. Note here that said connection element features L-like cross-section mating that if connection sections of the frames. Note also that connection element connection section makes a L-like cross-section long arm and features height representing the sum of frame height and difference in height. |
 Space telescope supporting girder / 2503048Invention relates to space telescopes and can be used for various girder and chassis structures with high requirements for geometric stability of dimensions under the effect of temperature. The space telescope supporting girder consists of longitudinal, transverse and diagonal cylindrical bars whose dimensions are stable under the effect of temperature and are joined with each other in intersection nodes. The longitudinal, transverse and diagonal bars are composite and are joined to each other by a toral basket shell on the larger axis. The toral basket shell is filled with thermometric fluid, wherein geometric dimensions of each of the composite cylindrical bars, the toral basket shell, characteristics of the used material and physical properties of the thermometer fluid are linked by the relationship: L = η 4,26 ⋅ b ( β − 3 α 1 ) ( 0,06 a 4 + R 1 2 ⋅ δ 1 2 ) α 2 ( 1 − μ 2 ) R 1 2 ⋅ δ 1 2 , where L is the total length of any of the composite bars; b, a denote the small and large semiaxis of the section of the toral basket shell; R1 is the radius of the middle surface of the toral basket shell; δ1 is the thickness of the toral basket shell; α1, α2 are coefficients of linear expansion of the material of the toral basket shell and the bars, respectively; β is the coefficient of volume expansion of the thermometer fluid; µ is the Poisson ratio of the material of the toral basket shell; η is a coefficient which indicates elasticity of the toral shell at points of connection thereof with the cylindrical bars. |
 Spacecraft head servicing hatch / 2497727Invention relates to rocketry. Spacecraft head servicing hatch comprises head cowl with flaps accommodating blisters for payload and cover. Proposed hatch is arranged at top part of one of said blisters provided with detachable cover. Servicing hatch has seal clamped by sections along its edges secured to head coal inner surface. Cutout is made in detachable cover bottom side to make ledges covering the blister outer part. Said blister outer part is furnished with protective wall secured to its crosswise surface by crosswise sections and connected to those of hatch seals. Detachable aerodynamic cowling with heat-resistance coating is secured at blister and sealed detachable cover. In servicing of payload made to protect its against the ingress of foreign matters in node cowl and there inside, attachments are arranged on hatch seals and node cowl cylindrical surface for detachable protective flute and detachable canvass. |
 Spacecraft head part and method of its assembly / 2497726Invention relates to aerospace engineering. Spaceship head comprises craft, nose cone and transfer module for docking to carrier rocket. Main frame is arranged in spacecraft above its centre of gravity whereto transfer module is attached by end split joint detachable in flight. Nose cowl is arranged at said main frame while craft is arranged inside transfer module. Sliding supports are arranged at transfer module inner surface to slide in guide surface of craft in separation of transfer module. Proposed method of assembly comprises attaching said transfer module with craft main frame. Craft is lowered in vertical position into transfer module. Transfer module sliding supports are fitted in craft guide surface. After attachment of craft with transfer module, nose cone is attachment to craft main frame. |
 Earth remote sounding spacecraft / 2493056Invention relates to spacecraft and onboard equipment design, mainly to thermostatic systems. Spacecraft integrates target hardware and service systems modules and is equipped with thermostatic jacket composed of rectangular parallelepiped. Three-layer cellular thermo panels with metal facing with heat pipes arranged there between are secured at sides of said parallelepiped. Jacket shell has a liquid heat carrier channel arranged at spacing equal that of heat pipes. Heat carrier has heat and mechanical contact with heat pipes. Channel length, heat pipe length and spacing between said pipes are selected to make jacket temperature differences along two mutually perpendicular directions not exceeding preset tolerances. One of thermo panel jacket walls composed of five-layer cellular panel allows a thermal contact between target hardware modules and service systems. Pipes of hydraulic main line are laid at thermo panel outer lining. End face thermo panel is composed of perforated metal plate for target hardware covers. Every plate hole is aligned with optical axis of appropriate hardware. End face thermo panel inner surface accommodates hydraulic main line pipes. Stable-size bearing structure (for example, of black-reinforced plastic) for target hardware is secured inside the jacket along spacecraft lengthwise axis. Service instrumentation of target hardware module is mounted at jacket top end wall. Jacket outer section is isolated from space by vacuum shield heat insulation. |
 Stringer (versions), method of developing stringer model, aerospace device (versions), aircraft (versions) and computer / 2492107Invention relates to stringer, method of developing stringer model with the help of computer, aerospace device and aircraft. Said stringer comprises base with first surface and second surface located opposite the first one, and rib with third and fourth surfaces. Stringer has L-like cross-section over its length and geometry varying along the part of its length with distance increasing along its length. Geometry variation represents a shift of said first surface toward second surface and fourth and third surfaces. Cross-section features, in fact, constant distance measured over cross-section surface between the points whereat cross-section intersects with first and second lines for all cross-sections along the part of its length. Proposed method of developing stringer model with the help of computer comprises preparing first data whereat stringer model base geometry is defined and distance from the base to imaginary plane varying along stringer length. Besides it comprises generation of second data whereat stringer model rib is defined including generation of local changes in rib geometry. Said first and second data are used for generation of stringer model. Method of making said elongated comprises making mould, placing composite material layers therein, and curing said layers. |
 Space device and aircraft, elongated element of space device or aircraft, method of making model of elongated element of space device or aircraft, and method of producing elongated element of space device or aircraft, and computer / 2486102Set of invention relates to elongated element of space device or aircraft composed of laminar structure.Said elongated element comprises base with opposed first and second surface, rib with third and fourth surfaces, and fifth surface arranged between first and third surfaces and connected therewith, and sixth surface arranged between second and fourth surfaces and bonded therewith. Elongated element includes change in geometry composed of first surface displacement toward second surface and reduction in fifth surface width. Method of making elongated element model for its production comprises preparation of first data indicating availability of changes in distance of base from reference plane, generation of second data to define rib geometry, and application of said first and second data for generation of element model. Decrease in risks of origination of defects in elongated element is ensured by making local variations in rib geometry using aforesaid model that comprise introducing angle section in the rib extending to elongated element base. Method of element production comprises preparing the mould, its profile being defined from elongated element model, laying layers of composite material into said mild, and hardening if said layers. |
 Reinforced shell of revolution from polymer composites / 2486101Invention relates to shells of structural parts made of polymer composites to be used in space and aircraft engineering and operated at higher loads. Reinforced shell of revolution consists of skin and set of ribs. Said ribs are arranged at skin outer side. Rib section features folding and rounded angle between vertical part and folding. Prior to forming the article, filling metallic sleeve-shape elements are arranged at intersections of ribs. Extreme annular ribs are furnished with bores and filling metallic sleeve-shape elements to be fitted in bores. |
 Two-stage ballistic space shuttle launch system / 2485025Invention relates to space engineering. Proposed system comprises rocket stages with propellant tanks and oxidiser (oxygen) tanks, sustainer rocket engines and stabilisation and orientation engines. First stage features cylindrical shape and is equipped with aft section, adapter and cowl. Sustainer rocket engines run on hydrogen. Tanks of both stages represent bearing structures with combined bottoms. Second stage is shaped to truncated cone with spherical bottoms is equipped with thermal protection. Both stages are equipped with landing supports. |
 Space device (versions) and aircraft (versions), elongated element of space device or aircraft (versions), composite spar, method of making its model and its production and computer / 2485011Invention relates to aerospace engineering, particularly, to elongated element and spar from laminar composite and method of developing their computer model and method of producing elongated element. Elongate element comprises base with first surface and second surface located opposite the first one, and rib with third and fourth surfaces. Cross-section of elongated element varies along its length with linear increase along said length of elongated element of structure of geodesic distance between first reference line located at first surface and second reference line located at third surface. Composite spar has top and bottom flanges jointed by rib and integral composite material extending between two opposite edges from top flange via rib to bottom flange. Geodesic distance over spar width measured along single layer between two opposite edges increases linear along single layer length. Method of making spar model comprises preparing first data on geometry of top and bottom flanges, nonlinear variation of spacing between flanges along spar length which, spar root, exceeds that nearby spar end, and generation of second data describing rib shape, that of top and bottom flange of spar model. Method of making said elongated comprises making mould, placing composite material layers therein, and curing said layers. |
 Liquid products replenishment system (versions) / 2244842Proposed system contacts autonomous subsystems located on cargo spacecraft and on space orbital station and including containers for liquid products with pipelines and valves. Container for liquid products of autonomous subsystem arranged on cargo spacecraft is made in form of bag of soft elastic cloth placed in rigid envelope and connected by flexible pipeline through hydraulic connector with change-over valve or through hydraulic connector with change-over valve and pump to similar container of other autonomous subsystem located on space orbital station. Space formed between bag and rigid envelope of autonomous subsystem located on cargo spacecraft communicates through valve with atmosphere of cargo spacecraft. Similar of container of autonomous subsystem located on space orbital station communicates through valve with atmosphere of space orbital station. Space orbital station is furnished with liquid wastes collecting system containing reservoir to be filled with liquid wastes in which space of bag is connected to semiconnector by means of flexible pipeline. Space formed between bag and rigid envelope communicates with atmosphere of space orbital station though valve or through valve and compressor. Invention makes it possible to create liquid products replenishment system providing utilization of liquid wastes from reservoir of autonomous subsystem at space orbital station by increasing efficiency of use of water container of autonomous subsystem of cargo spacecraft. |
 Device for rotation under condition of micro-gravitation (versions) / 2245282Proposed device has body with grooves (10a, 10b) and rotating shaft (30) whose both ends are fitted in bearings (11, 12) of grooves (10a, 10b). Lower end of shaft (30) is connected with engine (13). Four arms (24-27) are mounted horizontally and are secured on shaft (30) at one end; experimental boxes (20-23) are fitted on other ends. Objects of constant or increasing weight, such as plants or animals and human being are placed in boxes (20-23) where artificial micro-gravitation is formed by rotation for conducting experiments or work in space. Vibration of shaft (30) and boxes (20-23) is absorbed by bearings (11,12). Provision may be also made for special-purpose vibration generator. Side plates (1a-1d), acceleration sensors (2a-2d) and sensors (3a-3d) showing the distance between objects and plates are mounted in boxes (20-23). Mass of object is determined by means of computer unit on basis of signals received from sensors (2,3) at collision of object with side plate. These and similar signals from additional sensors are used for control of said vibration generator and motion of counter-weights (not shown) for elimination of unbalance of rotator and suppression of vibrations. |
 Module-type spacecraft / 2247683Proposed spacecraft has modules where service equipment is arranged and modules where target equipment and command and measuring devices are located. Optical devices of target equipment of infra-red range with cooled elements are mounted in central module. Radio equipment of on-board repeater is arranged in side modules whose position is changeable relative to position of central module. Optical and command and measuring devices are mounted on one frame at reduced coefficient of linear thermal expansion; they are combined with central module through three articulated supports. Cooled elements of optical devices are connected with radiators located beyond zone of thermal effect; service equipment module is provided with solar batteries having low dynamic effect on accuracy of spacecraft stabilization. Besides that, this module is provided with plasma engine whose working medium excludes contamination of said optical devices. |
 System of storage and delivery of gaseous oxygen / 2248459Proposed system includes high-pressure bottle and delivery main provided with starting valve, gas reducer, filters-current dischargers and adjusting valve. Filters-current dischargers mounted after starting valve and gas reducer are made in form of screen manufactured from corrosion-resistant metal at low specific resistance. Adjusting valve ensures required rate of oxygen flow through atomizing nozzle fitted at end of delivery main and communicated with consumer. |
 Device for locking articulation unit / 2250863Proposed device includes articulation with leaf spring secured on its part; spring has hole in its free end; secured as cantilever on other part is rod whose free end may be engageable with hole of leaf spring. Parts are provided with two stops for their engagement in fixed position; one stop is rigid for limitation of relative rotation of parts during opposite motion; other stop is spring-loaded for avoidance of backlash in joints of articulation unit due to elastic forces. As a result, damage of leaf spring is excluded at autonomous opening of swivel structural members at high rotational speeds. |
 Quick-release joint for connection of flying vehicle compartments / 2254270Proposed joint consists of compartments forming threaded pair for butt connection of them. External thread is made on cylindrical body 4 of one of compartments and projection is strengthened with frame 5 provided with threaded seat 7 where captive retainer 7 of threaded pair is placed. Threads of pair have longitudinal slots 10 whose depth exceeds depth of thread and their length is no less than length of thread. Slots give free passage for respective projections of external and internal threads; projections are screwed together and their longitudinal planes of symmetry are aligned. |
 Rotation apparatus operated in microgravity conditions / 2264331Rotation apparatus comprises casing (10), shaft (30) set in bearings (11) inside the casing, and motor (13) for rotating the shaft. Shaft (30) is provided with radial cantilevers (281) whose ends have a number of boxes (282) with experimental objects. The apparatus is provided with devices for damping vibration of the casing. Each of the devices has spring mechanism (255) that flexibly secures the casing to member (280) of the unmovable bearing and electromagnetic mechanism for setting. The latter comprises conductor (254) secured to member (280) and exciting coil (253) that embraces it and is mounted on the surface of casing (10). The coil is connected with the spring mechanism so that casing (10) is held by electromagnetic force that effects on conductor (254) when the coil is excited. The apparatus may be provided with a pickup that measures the space between casing (10) and member (280) of the bearing and control unit that receives the signals from the pickup. When the space exceeds a given value, the unit controls the current in exciting coil (253) to reduce casing vibration. |
 Lamellar sheathing / 2265520The invention is pertaining to the field of mechanical engineering, in particular, to production of constructions made out of composite materials for the high-precision hardware products of space and land designation, for example, conical nose cones of rocket carriers, transient bays, ring ramps. The lamellar sheathing is made out of layers of the fibrous material impregnated with a polymeric binding. Its each layer represents an unrolling or a part of a cone unrolling made in the form of a sector of a ring or a sector of a circle with a central angle β. In the capacity of the unidirectional fibrous material use a fibrous material impregnated with a polymeric binding. The central angle β of a sector of a ring or a sector of a circle makes 12-360 degrees. Each of layers of the lamellar sheathing consists of the placed butted to each other sectors with the equal central angle γ making 1-30 degrees. In each sector of one layer the fibers of the unidirectional fibrous material are located at the similar for this layer angle φ to the central axis of the sector equal to 0- ±90 degrees. The butts of the sectors of each subsequent layer are shifted in respect to the butts of the sectors of the previous layer at an angle δ composing a part of the central angle γ of the sector for. The technical result of the invention realization consists in creation of the sheathing with the stable physical-mechanical properties. |
 Micro-satellite / 2268205Some parts of onboard equipment in proposed satellite are secured on radiation surface on inner side of solar battery framework. Other parts are located in pressure container; number of parts is dictated by condition of retaining thermal mode of equipment in pressure container. Solar sensors are mounted on end face of pressure container coupled with micro-satellite separation system. Sensors for operation with ground stations and sensors of scientific equipment are located on other end face of pressure container. They are mounted on rectangular plate fitted with bracket in form of parallelepiped whose side faces carry scientific sensor equipment. Mounted on opposite surface of plate are sensors for operation with ground stations and extensible gravitational boom. Mounted on end cargo of boom are optical sensors. Four L-shaped antennae are located in parallel relative to faces of plate. |
 Method of forming thrust in solar radiant flux and device for realization of this method / 2268206Proposed method includes forming light-sensitive surface of solar sail and orientation of this surface in solar radiant flux. This surface is formed as cloud of finely-dispersed particles charged by solar photoelectrolizing. Stable shape close to sloping surface is imparted to cloud by means of electrostatic system of spacecraft. This system has at least one central and one concentric charge carriers of opposite signs. Control of shape and sizes of cloud may be performed by screening central charge or moving it relative to circular charge. |
FIELD: transport.
SUBSTANCE: invention relates to fixtures designed to mount the equipment at spacecraft with precise angular and linear adjustment of units at design tests. Device to mount assembly units (1) at article (9) comprises triangular (in cross-section) a structural prism (2). Assembly units (1) are fitted in prism (2) with the help of bolt (3) and locked an sealed by wire (4) and seal (5) at four points for every unit. Prism (2) is mounted with the help of bolts (7, 8) at adjustable base (6). Device design allows linear adjustment of the position of units (1) in lengthwise axis and perpendicular to axis: ΔZ, ΔY (with allowance Δ1 - for ranges ΔZ and Δ2 - for clearance ΔY) Position of said units can be adjusted in small range of angles α°± n' relative to article (9). Assembly units (1) can be independently assembled at structural prism (2). If required, prism (2) with assembly units can be removed from base (6) with no loss in precision of angular position of units (1).
EFFECT: linear adjustment of assembly units in two mutually perpendicular directions, high-precision angular adjustment.
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The invention relates to the installation of equipment on the aircraft, mostly space, the SPACECRAFT (SC) which require precise angular and linear adjustment units on the product (including the flight tests).
Device installation units on the product (including SATELLITES) is intended for linear control units in two mutually perpendicular directions to the required value, and for the angular control units with high accuracy in a small range of angles.
Of the patent literature known transport and technological unit consisting of an adjustable angle of the reference platform with respect to the frame, to the Assembly and preparation of blocks KA (see RF patent 2252179, IPC B64G 5/00, 04.02.2003).
The disadvantages of this device are the inability linear regulation provisions set aggregates relative to the reference platform and the inability to use these constructive decisions on the products that undergo flight development tests.
The technical result of this device is:
- provision of the required linear regulation units (up to + 45 mm) along one axis and (+/- 30 mm) along the axis perpendicular to this;
- ensuring accuracy of linear control units (+or-0.5 mm);
- provision of the required angular regulation together all units (up to + 1 degrees) around two mutually perpendicular axes;
- providing the required accuracy of the angular regulation units (+or-5 degrees);
- providing the possibility of Autonomous Assembly and testing of power units on the lens mounted on an adjustable base;
- providing of rigidity of a design under the inertial loading units at SC insertion (pH=6,5; HL=4,5);
- maintenance of required natural frequencies of the structure (not below 15 Hz);
- providing the required size of the gap between the regulatory basis and the plane mounting this reason on the product (not less than 50 mm);
- providing the possibility performance in a wide range of temperatures (-50 C...+50 C);
- providing technology and collection design in workshop conditions;
- provision of the minimum dimension of the construction adjustable base;
- provision of a minimum number of nodes and their minimum weight;
- maintenance of serviceability of the structure.
This technical result is achieved by the fact that the device installation units on the product contains Assembly of power structures with mountings of the units and adjustable basis with a pre-installed by the Assembly mounted on the product. In accordance with the invention of the power structure is made in the form of a triangular (cross-section) of the prism. Units of fastening units made with the possibility of linear regulation of position of each unit, which along triangular prisms made of the four slots and two risks with the function of opportunities linear regulation with the desired range, the location of each unit along prism. Adjustable base has the adjusting plate, three regulatory site that is hosted on the triangle corner regulation, and fixing the site, and six slots on the stove adjustment perpendicular to the longitudinal direction of a triangular prism, corresponding to six retaliatory grooves on a triangular prism, and the seats for the elements of control for indirect and direct method of angular measurement provisions units. The design of the regulated base is made under the scheme of the location of two of the three regulatory nodes within the outline of a triangular prism, and the third node is located opposite the units on the greatest possible distance for loop triangular prism within intended place for device installation units of the product to reduce the effects of a working body of the units on regulating unit.
Next, the device installation units on the product is explained in more detail using figures 1, 2, 3, 4, 5, 6A, 6b in the Cartesian coordinate system {0,X,Y,Z}.
Figure 1 shows a side view on the device setup units on the product, where two units 1 installed in a triangular prism 2 with bolted 3 controlkey with wire 4 and fillings 5 in four points for each unit 1 and triangular prism 2 is attached to a regulated basis with 6 bolted 7 controlkey with self-locking nuts 8, units 1 in a triangular prism 2 on the regulated under 6 are attached to the article 9, which sets the Assembly. The Cartesian coordinate system {0,X,Y,Z} is a base for the product, and 9. UN - rated coordinate adjustable base 6; Z N - nominal coordinate triangular prism 2; ΔY - the gap between adjustable base 6 and article 9; ΔZ - range line regulation units 1 with a triangular prism 2 along the Z axis; Δ1 - supply range ΔZ; Δ2 - supply gap ΔY; α - degree angle of installation of units 1 (typical); ±n' - tolerance angle of? degrees.
Figure 2 shows the risks 10, 11 for linear control units 1 together with a triangular prism 2 along the Z-axis (see figure 1).
Figure 3 shows the device installation units on the product in horizontal projection, where the two units 1 installed in a triangular prism 2 and adjustable base 6, which is attached to the article 9 where, there are also elements of control (EC) 12 for the indirect method angular measurements or EC of 13 for direct method of angular measurement provisions of units 1, the number and place of installation EC 12, 13 scheme determines the angular measurements to articles 9 and units 1. The Cartesian coordinate system {0,X,Y,Z} is a base for the product, and 9. HN - rated coordinate bolted connection mounting of the first unit 1 to the triangular prism 2; HN - rated coordinate bolted connection mounting of the second unit 1 to the triangular prism 2, Δ - range line regulation units 1 along the X-axis; Δ3 - supply range Δ; 1 - degree angle seat 14 on a triangular prism 2 of the first unit 1 (typical); 2 - degree angle seat 15 of the second unit 1 (typical); γ1 - degree angle of installation of the first unit 1 (typical); γ2 - degree angle of installation of the second unit 1 (typical); ±n' - tolerance angles 1°, 2°, γ1°, γ2 degrees. Thus corners 1°, 2° measured in an indirect method of measurement of the angular position of units 1 and the corners γ1°, γ2 OC in direct method of measurement.
Figure 4 shows a section of the device installation units of the product as a triangular prism 2, which shows the triangle angle regulation 16 and design adjustable base 6, it stove adjusting 17, regulating unit 18 (three pieces), fixing the site 19. Also listed slots (six units) 20 on a triangular prism 2 and response slots (six units) 21 on the stove adjusting 17. And also the Δ - base of the triangle of regulation 16 along the X axis (see figure 1, 3) and ΔZ - base of the triangle of regulation 16 along the Z-axis (see figure 1, 3). Δ, ΔZ together with the design of the regulatory node 18 determine the angular step regulation of Reg. Thus Reg<n, where n is the tolerance for angles α°, γ1 degrees(1 degrees), γ2 degrees(2 degrees) installation of units 1 (see figure 1, 3). If necessary, n can be different for the specified angle is determined by the requirements for installation of units 1). Also ΔZ - range line regulation units 1 with a triangular prism 2, is determined by the length of the groove 20; ΔZ - range line regulation units 1 with a triangular prism 2, is determined by the length of the groove 21. The ratio of the lengths of grooves 20, 21 is defined by the design of a triangular prism 2 and plate adjustment 17, and the range ΔZ=ΔZ+ΔZ. Full range of linear regulation units 1 along the Z-axis: ±(ΔZ+Δ1).
Figure 5 shows a triangular prism 2 boarding 14 surface for the first unit 1 and 15 for the second unit 1, where on the surface of 14 is a rectangular hole 22 for installation of the first unit 1 and four slots 23 for linear regulation of the first unit 1 along the X axis within the range of regulating and measuring the nominal and finite linear position of the first unit 1 performed risks 24; also on the surface of 15 is a rectangular hole 25 for installation of the second unit 1 and four slots 26 for linear regulation of the second unit 1 along the X axis within the range of regulating and measuring the nominal and finite linear position of the first unit 1 performed risks 27. Also listed Δ - the distance between the corresponding coordinates In, HN and the basis of units of 1, defined by the construction of units 1. Full range of linear regulation units 1 along the X-axis:±(Δ+Δ3).
On figa and 6b shows the units 1 on a triangular prism 2, where the first and second units 1 are installed on the appropriate Seating surfaces 14 and 15 triangular prism 2, and indicated EC 12 and 13 (see figure 1, 3) for indirect and direct method of angular measurement provisions of units 1, respectively.
When mounted units 1 on article 9 units 1 is installed on a triangular prism 2 in nominal linear position, combining risks linear regulation 24, 27 with the end of the corresponding unit 1 and triangular prism 2 with units 1 set in nominal linear position adjustable base 6 fixed in nominal angular position in relation to articles 9, combining risks linear regulation 10, 11; then establish, if necessary, the required linear position, moving the required within the range line regulation-size units 1 regarding risok 24, 27 and 10, 11 (together with a triangular prism 2); and adjust, if necessary, the angular position of units 1 on a regulated basis 6 within the range of the corner of regulating, measuring indirect or direct method actual angular position of units 1 regarding articles 9.