CN111071488A - Instrument mounting panel structure of carrier rocket - Google Patents
Instrument mounting panel structure of carrier rocket Download PDFInfo
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- CN111071488A CN111071488A CN201911389825.6A CN201911389825A CN111071488A CN 111071488 A CN111071488 A CN 111071488A CN 201911389825 A CN201911389825 A CN 201911389825A CN 111071488 A CN111071488 A CN 111071488A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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Abstract
The invention discloses an instrument mounting plate structure of a carrier rocket, which comprises: the instrument cabin is in the shape of a revolving body; the instrument mounting plate is arranged in the instrument cabin, and the periphery of the instrument mounting plate is connected with the inner wall of the instrument cabin through a corner box assembly; the upper surface of the instrument mounting plate is provided with a plurality of instrument mounting positions for mounting instrument equipment, and the upper surface of the instrument mounting plate corresponding to the axis of the instrument cabin is provided with a hoop assembly for mounting an inertial measurement unit. The instrument mounting plate structure of the carrier rocket has the characteristics of open space, simplicity and convenience in assembly, firmness and reliability in instrument equipment mounting, high precision of the inertial unit mounting position and the like, meets the mounting requirements of various carrier rocket instrument equipment through reasonably designing the instrument mounting scheme, reduces the weight of a structural system and improves the carrying capacity.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an instrument mounting plate structure of a carrier rocket.
Background
Satellites rely primarily on launch vehicles to launch into space. During operation, fire takeoff, program turning, separation of each stage, attitude control, guidance, navigation and the like of the rocket need to use various instruments and equipment to complete related actions, so that a large amount of instruments and equipment need to be installed on the carrier rocket. Most of the devices are installed in an instrument cabin and enter the orbit along with the satellite, so the design of an instrument installation structure is very important.
At present, the shell of an instrument cabin is mostly of a cylinder section structure, a large amount of instrument equipment needing to be installed in the instrument cabin is mostly installed on the inner wall of the shell of the instrument cabin in a side-hanging or cantilever type mode, in order to meet the installation requirements of the large amount of instrument equipment, the size of the shell of the instrument cabin needs to be designed to be large enough to enable the inner wall of the shell to provide enough installation space, so that the whole instrument cabin is heavy, the space of the inner wall of the shell of the instrument cabin is narrow, and the installation of the large amount of instrument equipment is inconvenient.
Therefore, a carrier rocket instrument installation plate structure which is open in space, simple and convenient to assemble, capable of meeting installation requirements of various carrier rocket instrument devices and low in self weight of a structural system needs to be designed.
Disclosure of Invention
Therefore, the invention aims to solve the technical problems that the instrument cabin is heavy and the instrument equipment is inconvenient to install in the prior art, so that the instrument mounting plate structure of the carrier rocket is provided.
In order to solve the technical problems, the technical scheme of the invention is as follows:
an instrument-mounting plate structure for a launch vehicle, comprising:
the instrument cabin is in the shape of a revolving body;
the instrument mounting plate is arranged in the instrument cabin, and the periphery of the instrument mounting plate is connected with the inner wall of the instrument cabin through a corner box assembly; the upper surface of the instrument mounting plate is provided with a plurality of instrument mounting positions for mounting instrument equipment.
Furthermore, the instrument mounting plate is in a cross shape, and four end parts of the instrument mounting plate are connected to the inner wall of the instrument cabin through the corner box assembly.
Further, the lower surface of the instrument mounting plate is provided with a reinforced structure.
Furthermore, the instrument mounting plate comprises a transverse plate and a longitudinal plate which are integrated and perpendicular to each other, and the intersection center of the transverse plate and the longitudinal plate is positioned on the axis of the instrument cabin; the reinforced structure includes the edge a plurality of horizontal reinforcements that the length direction of diaphragm extends and the interval sets up and follow a plurality of vertical reinforcements that the length direction of vertical slat extends and the interval sets up.
Furthermore, a grid reinforcement structure is arranged on the inner wall surface of the instrument cabin, and a plurality of connecting plates corresponding to the four end parts of the instrument mounting plate are connected to annular convex ribs of the grid reinforcement structure; the corner box assembly comprises: the top wall is respectively connected with the lower surface of the instrument mounting plate and the lower surface of the connecting plate, the first side wall is connected with the inner wall of the instrument cabin, and the second side wall is connected with the reinforcement structure; the top wall, the first side wall and the second side wall are perpendicular to each other two by two.
Further, the corner box assembly comprises:
the first corner boxes are at least four and are respectively connected between the four corners of the lower surface of the transverse plate and the inner wall of the instrument cabin;
and the second corner boxes are at least four and are respectively connected between the four corners of the lower surface of the longitudinal plate and the inner wall of the instrument cabin.
Further, the width of longitudinal plate is greater than the width of diaphragm, the corner box subassembly still includes:
and at least two third corner boxes are arranged and are respectively connected between the middle positions of the two ends of the longitudinal plate and the inner wall of the instrument cabin.
Furthermore, the instrument mounting plate is correspondingly provided with a mounting boss on the lower surface of the instrument mounting position.
Furthermore, the upper surface of the instrument mounting plate corresponding to the axis of the instrument cabin is provided with a hoop assembly for installing the inertial measurement unit.
Further, the embracing ring assembly comprises:
the first holding ring and the second holding ring are connected to the instrument mounting plate and enclose to form the inertial unit mounting space, and first mounting holes which are transversely arranged and used for fixing the inertial unit along the circumferential direction of the inertial unit are formed in the first holding ring and the second holding ring;
and the inertial unit leaning block is connected to the instrument mounting plate, and a second mounting hole which is vertically arranged and is used for fixing the inertial unit along the axial direction of the inertial unit is formed in the inertial unit leaning block.
The technical scheme of the invention has the following advantages:
1. according to the instrument mounting plate structure of the carrier rocket, the instrument mounting plate is connected in the instrument cabin through the angle box assembly, so that the instrument mounting plate can be reliably connected; and the upper surface of instrument installation board can be for a large amount of instrument installation positions that instrument equipment provided, compares with the mode of instrument equipment hanging installation at the instrument shelter inner wall among the prior art, and the space of instrument installation board top is more open, makes things convenient for instrument equipment's installation fixed, need not the size of increase instrument shelter and also can satisfy a large amount of instrument equipment's installation demand, can reach the effect that lightens instrument shelter overall structure's dead weight, improvement rocket carrying capacity.
2. The instrument mounting plate structure of the carrier rocket, provided by the invention, has the advantages that the upper surface of the cross-shaped instrument mounting plate is provided with a large enough mounting plane, enough instrument mounting positions can be arranged, and the instrument can be conveniently and fixedly arranged.
3. According to the instrument mounting plate structure of the carrier rocket, the arrangement of the reinforced structure on the instrument mounting plate can improve the structural strength and the bearing capacity of the instrument mounting plate, and the self weight of the instrument mounting plate is reduced under the condition that the instrument mounting plate meets the design requirement; and a stable operation of mounting the instrument thereon can be ensured.
4. According to the instrument mounting plate structure of the carrier rocket, the integrally designed instrument mounting plate can improve the structural strength of the instrument mounting plate, so that the self weight of the instrument mounting plate is reduced; and the reinforced structure that the longitudinal reinforcement that sets up by a plurality of intervals set up transversely adds muscle and a plurality of intervals set up becomes, can ensure that the rigidity and the bearing capacity of instrument mounting panel each position can both satisfy the designing requirement, the design distribution of a large amount of instruments on the instrument mounting panel of being convenient for.
5. According to the instrument mounting plate structure of the carrier rocket, the angle box assembly connects the connecting plate on the inner wall of the instrument cabin and the instrument mounting plate together through the top wall of the angle box assembly, and the connection reliability between the instrument mounting plate and the instrument cabin can be improved through the mode that the first side wall is connected with the inner wall of the instrument cabin and the second side wall is connected with the reinforcement structure on the instrument mounting plate.
6. According to the instrument mounting plate structure of the carrier rocket, the instrument mounting plate and the instrument cabin are fixedly connected by adopting the angle boxes of various types, so that the connection reliability is greatly improved.
7. According to the instrument mounting plate structure of the carrier rocket, due to the design of the mounting bosses on the instrument mounting plate, the local structural strength of the instrument mounting plate can be improved, and the damage of the instrument mounting plate is reduced.
8. According to the instrument mounting plate structure of the carrier rocket, the hoop component is arranged on the upper surface of the axis of the instrument cabin, so that high positioning accuracy can be provided for the inertial measurement unit.
9. The instrument mounting plate structure of the carrier rocket provided by the invention is provided with the hoop component consisting of the first hoop, the second hoop and the inertial set leaning block, and the inertial set can be fixed along the axial direction and the circumferential direction of the inertial set, so that reliable connection is provided for the inertial set.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic diagram of a design of a launch vehicle instrument mounting plate structure in an embodiment of the invention;
FIG. 2 is a schematic view of an instrument mounting plate coupled to an instrument pod in an embodiment of the present invention;
FIG. 3 is a schematic view of the upper surface of an instrument mounting plate in an embodiment of the invention;
FIG. 4 is a schematic view of the lower surface of an instrument mounting plate in an embodiment of the invention;
FIG. 5 is a schematic view of a mounting structure of the hoop assembly on the instrument mounting plate according to the embodiment of the invention;
FIG. 6 is a schematic structural diagram of a first corner box according to an embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a second corner box according to an embodiment of the present invention;
fig. 8 is a schematic structural diagram of a third corner box in an embodiment of the present invention.
Description of reference numerals: 1. an instrument pod; 11. a grid reinforcement structure; 12. a connecting plate; 2. an instrument mounting plate; 21. a transverse plate; 22. a longitudinal plate; 23. transversely reinforcing ribs; 24. longitudinally reinforcing; 25. mounting a boss; 3. a corner box assembly; 31. a first corner box; 32. a second corner box; 33. a third corner box; 301. a top wall; 302. a first side wall; 303. a second side wall; 4. a hoop component; 41. a first embracing ring; 42. a second embracing ring; 43. an inertial assembly leaning block; 5. inertial measurement unit; 6. the flap is maintained.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
An instrument mounting plate structure of a launch vehicle as shown in fig. 1-8 includes an instrument pod 1 and an instrument mounting plate 2 disposed in the instrument pod 1. The instrument chamber 1 is a barrel structure in the shape of a revolving body, openings are formed in two ends of the barrel structure, and a grid reinforcement structure 11 is arranged on the inner wall of the barrel structure. The periphery of instrument mounting panel 2 passes through the inner wall fixed connection of angle box subassembly 3 with instrument cabin 1, and the upper surface of instrument mounting panel 2 is equipped with a plurality of instrument installation positions that supply instrument equipment to install.
The instrument mounting plate 2 is connected in the instrument cabin 1 through the angle box assembly 3, so that the instrument mounting plate 2 can be reliably connected; and the upper surface of instrument mounting panel 2 can be for a large amount of instrument installation positions that instrument equipment provided, compare with the mode of instrument equipment hanging installation at instrument shelter 1 inner wall among the prior art, the space of instrument mounting panel 2 top is more open, makes things convenient for instrument equipment's installation fixed, need not the size of increase instrument shelter 1 and also can satisfy a large amount of instrument equipment's installation demand, can reach the effect that alleviates 1 overall structure's of instrument shelter dead weight, improvement rocket carrying capacity.
In this embodiment, the instrument mounting plate 2 is in a cross shape, the upper surface of the instrument mounting plate is a flat surface, and four ends of the instrument mounting plate 2 are connected to the inner wall of the instrument chamber 1 through the corner box assemblies 3. The upper surface of the cross-shaped instrument mounting plate 2 is provided with a large enough mounting plane, so that enough instrument mounting positions can be arranged, and the instrument can be conveniently and fixedly mounted. In other embodiments, the instrument mounting plate 2 may also have a shape of a "m" or other shapes as long as it can be stably fixed on the inner wall of the instrument pod 1 and the upper surface may have a mounting space for the installation of instrument equipment.
In the present embodiment, the lower surface of the instrument-mounting plate 2 is provided with a reinforcement structure. The reinforced structure can improve the structural strength and the bearing capacity of the instrument mounting plate 2, and reduce the dead weight of the instrument mounting plate 2 under the condition of ensuring that the instrument mounting plate 2 meets the design requirement; and a stable operation of mounting the instrument thereon can be ensured.
Specifically, the instrument mounting plate 2 includes a transverse plate 21 and a longitudinal plate 22 that are integrated and perpendicular to each other, and the intersection center of the transverse plate 21 and the longitudinal plate 22 is located on the axis of the instrument chamber 1. The instrument mounting panel 2 of integrated design can improve the structural strength of instrument mounting panel 2, and then reduces the dead weight of instrument mounting panel 2.
Specifically, the reinforcement structure includes a plurality of transverse reinforcements 23 extending in the longitudinal direction of the transverse plate 21 and arranged at intervals, and a plurality of longitudinal reinforcements 24 extending in the longitudinal direction of the longitudinal plate 22 and arranged at intervals. The reinforced structure formed by the staggered arrangement of the plurality of transverse reinforced ribs 23 and the plurality of longitudinal reinforced ribs 24 can ensure that the rigidity and the bearing capacity of each position of the instrument mounting plate 2 can meet the design requirements, and a large number of instruments can be conveniently designed and distributed on the instrument mounting plate 2.
In this embodiment, the inner wall surface of the instrument chamber 1 is provided with a grid reinforcement structure 11, and four connecting plates 12 corresponding to four end positions of the instrument mounting plate 2 are connected to annular convex ribs of the grid reinforcement structure 11. The corner box assembly 3 includes: a top wall 301 connected to the lower surface of the instrument mounting plate 2 and the lower surface of the connecting plate 12, respectively, a first side wall 302 connected to the inner wall of the instrument pod 1, and a second side wall 303 connected to the reinforcement structure; the top wall 301, the first side wall 302 and the second side wall 303 are perpendicular to each other two by two; and are provided with a plurality of mounting through holes for connection with other components. The corner box assembly 3 is connected with the connecting plate 12 on the inner wall of the instrument cabin 1 and the instrument mounting plate 2 through the top wall 301 of the corner box assembly, and can improve the connection reliability between the instrument mounting plate 2 and the instrument cabin 1 through the mode that the first side wall 302 is connected with the inner wall of the instrument cabin 1 and the second side wall 303 is connected with the reinforcement structure on the instrument mounting plate 2.
In the present embodiment, the corner box assembly 3 includes a plurality of different types of corner boxes, namely a first corner box 31 and a second corner box 32. The first corner boxes 31 are at least four and are respectively connected between four corners of the lower surface of the transverse plate 21 and the inner wall of the instrument chamber 1; the second corner boxes 32 also have at least four corners, and are connected between the four corners of the lower surface of the vertical plate 22 and the inner wall of the instrument pod 1. The instrument mounting plate 2 and the instrument cabin 1 are fixedly connected by the angle boxes of various types, so that the connection reliability is greatly improved.
In the present embodiment, since the width of the vertical plate 22 is larger than that of the horizontal plate 21, four third-angle boxes 33 are further connected between the middle positions of the two ends of the vertical plate 22 and the inner wall of the instrument chamber 1 in order to improve the connection reliability of the vertical plate 22 and the inner wall of the instrument chamber 1.
In the present embodiment, the instrument mounting plate 2 is integrally formed with a mounting boss 25 corresponding to the lower surface on which the instrument mounting portion is provided. The design of the installation boss 25 can improve the local structural strength of the instrument installation plate 2 and reduce the phenomenon that the instrument installation plate 2 is damaged due to external force.
In this embodiment, in order to facilitate the maintenance of various instruments in the instrument pod 1, the sidewall of the instrument pod 1 is further opened with a plurality of maintenance flaps 6, and the maintenance flaps 6 are opened to perform the maintenance of the instruments and equipment in the instrument pod 1.
In the embodiment, the upper surface of the instrument mounting plate 2 corresponding to the axis of the instrument chamber 1 is fixedly connected with a hoop assembly 4 for mounting an inertial measurement unit 5. The embracing ring component 4 is arranged on the upper surface of the axis of the instrument cabin 1, and can provide higher positioning precision for the inertial measurement unit 5. Specifically, the hoop assembly 4 includes a first hoop 41, a second hoop 42 and an inertia block 43; the first holding ring 41 and the second holding ring 42 are respectively connected to the instrument mounting plate 2 and enclose to form an inertial unit 5 mounting space, and the side walls of the first holding ring 41 and the second holding ring 42 are respectively provided with a first mounting hole which is transversely arranged and used for fixing the inertial unit 5 along the circumferential direction of the inertial unit 5; the inertial measurement unit rest block 43 is fixedly connected to the instrument mounting plate 2, and a second mounting hole which is vertically arranged and fixes the inertial measurement unit 5 along the axial direction of the inertial measurement unit 5 is formed above the inertial measurement unit rest block 43. The hoop assembly 4 composed of the first hoop 41, the second hoop 42 and the inertial set leaning block 43 can fix the inertial set 5 along the axial direction and the circumferential direction of the inertial set 5, and provides reliable connection for the inertial set 5.
In the following, the embodiment of the present invention will be described in detail, wherein the instrument chamber 1, the instrument mounting plate 2, the corner box assembly 3 and the hoop assembly 4 are made of aluminum alloy materials. After the instrument cabin 1, the instrument mounting plate 2, the corner box assembly 3, the hoop assembly 4 and other accessory components are independently assembled, the components are connected into a whole by bolts. Each instrument on the upper surface of the instrument mounting plate 2 is used for mounting various instrument devices including the inertial measurement unit 5, and the instrument devices are also fixed on the instrument mounting plate 2 in a bolt connection mode; the inerter 5 is embodied as an optical fiber inerter 5 in the present embodiment. The first corner box 31, the second corner box 32 and the third corner box 33 are all manufactured by aluminum alloy machining.
In a specific embodiment of this embodiment, the diameter of the instrument pod 1 is 1.2m, the height is 0.7m, the thickness of the end frames at the two ends of the instrument pod 1 is 10mm, and the height of the internal grid ribs is 12mm and the width is 2 mm. The instrument chamber 1 is made of aluminum alloy 2A14 forgings and is machined and formed.
The instrument mounting plate 2, the first embracing ring 41, the second embracing ring 42, the inertial assembly leaning block 43, the first corner box 31, the second corner box 32 and the third corner box 33 are machined from aluminum alloy, and the materials are aluminum alloy 2A14 plates.
The maintenance opening cover 6 is made of an aluminum alloy 2A12 plate, and is formed by sheet metal machining. The opening of the maintenance port cover 6 had a diameter of 200mm and a thickness of 3 mm.
The panel foundation thickness of the instrument mounting plate 2 is 2mm, and a mounting boss 25 with the thickness of 10mm is formed on the part of the instrument mounting plate 2 for mounting instrument equipment. The lower surface of the instrument mounting plate 2 has 4 groups of transverse reinforcements 23 and 7 groups of longitudinal reinforcements 24, the reinforcement distance is 60mm, the reinforcement thickness is 4mm, and the reinforcement height is 35 mm.
The radius of a circle formed by the first embracing ring 41 and the second embracing ring 42 is 86mm, and the height is 99 mm; the thickness of the flanges at the bottoms of the first embracing ring 41 and the second embracing ring 42 is 3 mm; the thicknesses of the vertical sides of the first embracing ring 41 and the second embracing ring 42 are 5mm, and weight reducing openings of 37mm multiplied by 40mm are designed; two triangular reinforcing ribs with the thickness of 3mm are arranged on the outer sides of the first embracing ring 41 and the second embracing ring 42.
The inertial mass 43 has a thickness of 17mm, a length of 46mm and a width of 42 mm.
And (4) processing each component and then carrying out final assembly.
In the process of installing the instrument equipment in the instrument cabin 1, firstly, the four first corner boxes 31, the four second corner boxes 32 and the four third corner boxes 33 are respectively installed at corresponding positions on the inner wall of the instrument cabin 1; then the instrument mounting plate 2 is mounted on the corner box component 3; and then the first hoop, the second hoop and the inertial set leaning block 43 are arranged on the instrument mounting plate 22. After the steps are completed, various instruments and equipment including the inertial measurement unit 5 can be installed on the instrument installation plate 2, and finally the maintenance opening cover 6 is installed on the instrument cabin 1.
In an alternative embodiment of the present disclosure, the number of the first corner boxes 31, the second corner boxes 32, and the third corner boxes 33 may be as described herein, or may be other numbers.
In summary, in the instrument mounting plate structure of the launch vehicle provided by the embodiment of the invention, the instrument mounting plate 2 is arranged in the instrument cabin 1, and the instrument mounting plate 2 is connected with the instrument cabin 1 through the angle box assembly 3, so that the instrument mounting plate 2 can be reliably connected; and the upper surface of the instrument mounting plate 2 can provide a large amount of instrument mounting positions for instrument equipment, has the characteristics of open space, simple and convenient assembly, firm and reliable instrument equipment mounting, high precision of the mounting position of the inertial unit 5 and the like, meets the mounting requirements of various carrier rocket instrument equipment, lightens the weight of a structural system and improves the carrying capacity by reasonably designing the instrument mounting scheme.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911389825.6A CN111071488A (en) | 2019-12-27 | 2019-12-27 | Instrument mounting panel structure of carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911389825.6A CN111071488A (en) | 2019-12-27 | 2019-12-27 | Instrument mounting panel structure of carrier rocket |
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| CN111071488A true CN111071488A (en) | 2020-04-28 |
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| CN201911389825.6A Pending CN111071488A (en) | 2019-12-27 | 2019-12-27 | Instrument mounting panel structure of carrier rocket |
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| CN109911246A (en) * | 2019-02-20 | 2019-06-21 | 上海卫星工程研究所 | Spacecraft composite structure is connected suitable for point type |
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| US5662290A (en) * | 1996-07-15 | 1997-09-02 | Versatron Corporation | Mechanism for thrust vector control using multiple nozzles |
| RU2175113C1 (en) * | 2000-03-14 | 2001-10-20 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Process of correction of perpendicularity of axis of rotor of gyroscope and gyroscopic instrument |
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