CN111102971B - Small rotor gyro with rapid heat conduction structure - Google Patents
Small rotor gyro with rapid heat conduction structure Download PDFInfo
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- CN111102971B CN111102971B CN201911369913.XA CN201911369913A CN111102971B CN 111102971 B CN111102971 B CN 111102971B CN 201911369913 A CN201911369913 A CN 201911369913A CN 111102971 B CN111102971 B CN 111102971B
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- motor
- inner ring
- gyroscope
- gyro
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/02—Rotary gyroscopes
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/02—Rotary gyroscopes
- G01C19/04—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
- G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
- G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
- G01C21/18—Stabilised platforms, e.g. by gyroscope
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Gyroscopes (AREA)
Abstract
The utility model provides a small-size rotor top with quick heat conduction structure, including the top shell, top shell inside equipment has gyro motor, top inner ring subassembly, top outer ring subassembly, torque generator and biax angle sensor, and gyro motor, torque generator, biax angle sensor and top shell's appearance structure all adopts spherical symmetrical structure, carries out the evacuation after the inside part equipment of top shell is accomplished and fills helium, and top inner ring subassembly includes the inner ring frame, all is equipped with heat radiation structure on gyro motor and the inner ring frame. The invention adopts compact spherical symmetrical design, combines helium gas inlet sealing and local heat dissipation structure, improves heat dissipation performance of the small rotor gyroscope, prolongs service life of the gyroscope, has strong environmental adaptability and high reliability, has large tracking measurement rate range, and ensures that all performance indexes of the gyroscope meet the development requirement of a host.
Description
Technical Field
The invention belongs to the technical field of inertial device engineering in inertial navigation and control technology, and particularly relates to a small rotor gyroscope with a rapid heat conduction structure.
Background
The small rotor gyroscope is a matching product of a certain missile, is arranged on a double-shaft stable platform of a missile seeker, and utilizes the dead axle and precession of the gyroscope to stabilize and control the double-shaft stable platform, so that an accurate inertial reference standard is provided for a radar seeker angle measurement system, and the missile can accurately capture and track a dynamic target in the air. The small rotor gyroscope is composed of main components such as a gyroscope motor rotating at a high speed (not lower than 54000 r/min), a gyroscope inner ring component, a gyroscope outer ring component, two permanent magnet torque generators, two induction type double-shaft angle sensors and the like. The main components are assembled in the top shell, the upper cover, the lower cover and the top shell are sealed by welding, and inert gas-helium gas is filled in the top. Working principle of small rotor gyro: the high-speed rotating gyro rotor main shaft has directional stability in an inertia space, and when external moment is applied to the gyro inner ring shaft and the gyro outer ring shaft, the gyro rotor main shaft generates precession. For the small rotor gyroscope, the small rotor gyroscope is required to be small in size and compact in structure by the flying body guide head, so that the heat dissipation structure of the traditional gyroscope cannot be directly applied to the gyroscope. It is therefore necessary to design a suitable heat dissipation structure for it.
Disclosure of Invention
The invention solves the technical problems that: the invention provides a small rotor gyroscope with a rapid heat conduction structure, which adopts a compact spherical symmetrical design, combines a helium sealing and local heat dissipation structure, improves the heat dissipation performance of the small rotor gyroscope, prolongs the service life of the gyroscope, has strong environmental adaptability, high reliability and large tracking and measuring speed range, and ensures that all performance indexes of the gyroscope meet the development requirements of a host.
The invention adopts the technical scheme that: the utility model provides a small-size rotor top with quick heat conduction structure, includes the top shell, top shell inside equipment has top motor, top inner ring subassembly, top outer ring subassembly, moment generator and biax angle sensor, top inner ring subassembly and top outer ring subassembly mutually perpendicular alternately install in the top shell, the top motor is installed in top inner ring subassembly center the top motor is taken in the top shell inside, the lower part is all installed moment generator and biax angle sensor as the center, top motor, moment generator, biax angle sensor and top shell's appearance structure all adopts spherical symmetrical structure, carry out the evacuation after the inside part equipment of top shell is accomplished and fill helium, top inner ring subassembly includes inner ring frame and top room upper and lower cover, all be equipped with heat radiation structure on top motor and the inner ring frame.
In the preferable mode of the technical scheme, the heat dissipation structure between the gyro motor and the inner ring frame comprises an annular heat conduction air gap and an air guide hole; the top motor is provided with a motor support shaft, the end part of the top motor is provided with a motor end cover, the motor end cover is provided with a motor via hole, and the motor support shaft penetrates through the motor via hole on the motor end cover and forms an annular heat conduction air gap with an installation gap between the motor support shaft and the motor via hole; the air guide holes are arranged on the inner ring frame.
In the preferred mode of the technical scheme, the inner ring frame is provided with the air holes at four places in central symmetry, and the number of the air holes at each place on the inner ring frame is 4 and the aperture sizes are different.
In the preferable mode of the technical scheme, the outer rotor of the gyro motor is of a spherical structure made of tungsten alloy.
Compared with the prior art, the invention has the advantages that:
1. the small and medium-sized rotor gyroscopes in the scheme are structurally and totally designed in a compact spherical symmetrical mode, so that three parts of the gyroscopes, namely a gyroscopic motor, a moment generator which is arranged vertically symmetrically and a double-shaft angle sensor which is arranged vertically symmetrically are guaranteed, uniformity of heating and heat conduction is avoided, and heat stress concentration is avoided; the spherical structure of the gyro motor increases the outer surface area of the gyro motor and improves the heat dissipation performance; meanwhile, helium is filled for sealing after the performance adjustment of the gyroscope is completed, and a heat dissipation structure between a gyroscope motor and an inner ring frame is combined, so that the gyroscope is subjected to heat conduction by utilizing a metal material of the gyroscope, the rapid heat conduction performance of the gyroscope is optimized, the heat dissipation performance of the gyroscope of the small rotor is improved, the service life of the gyroscope is prolonged, the gyroscope has strong environmental adaptability and high reliability, the tracking measurement rate range is large, and all performance indexes of the gyroscope of the small rotor are ensured to meet the development requirements of a host machine.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic diagram of a gyro motor annular heat conducting air gap according to the present invention;
FIG. 3 is an enlarged schematic view of the annular thermally conductive air gap shown in section A of FIG. 2;
FIG. 4 is a schematic view of the structure of the air vent on the inner ring frame according to the present invention;
FIG. 5 is a schematic view of the structure of FIG. 4 in section E-E.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the present disclosure, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation. The term "comprising" an element defined by the term "comprising" does not exclude the presence of other identical elements in a process, method, article or apparatus that comprises the element.
Referring to fig. 1-5, embodiments of the present invention are described,
the utility model provides a small-size rotor top with quick heat conduction structure, is shown as the fig. 1, includes top shell 6, top shell 6 inside package has top motor 1, top inner ring subassembly 2, top outer ring subassembly 3, moment generator 4 and biax angle sensor 5, top inner ring subassembly 2 and top outer ring subassembly 3 mutually perpendicular cross mounting in top shell 6, top motor 1 installs in top inner ring subassembly 2 center the top shell 6 is inside to top motor 1 as the center, moment generator 4 and biax angle sensor 5 are all installed to the lower part.
The appearance structures of the gyro motor 1, the moment generator 4, the double-shaft angle sensor 5 and the gyro shell 6 all adopt spherical symmetrical structures, the compact spherical symmetrical design is adopted in the structure of the small-sized rotor gyro, three parts of the gyro, namely the gyro motor, the moment generator which is arranged vertically symmetrically and the double-shaft angle sensor which is arranged vertically symmetrically are ensured, the uniformity of heating and heat conduction is avoided, and the concentration of thermal stress is avoided.
The component inside the gyro shell 6 is vacuumized and filled with helium after being assembled, the helium is vacuumized and filled inside the gyro to replace air used by a traditional gyro, and the reliability, the heat conduction and the heat dissipation effects are remarkable, and the method is as follows: (1) helium belongs to inert gas, has no oxidizing property, has stable chemical property, can effectively prevent oxidation of metal structural members in the gyroscope, obviously slows down ageing of nonmetallic members such as grease, glue and the like, and finally ensures the working life and the storage life of the gyroscope; (2) the coefficient of heat conductivity (0.1426W/(m.k) of helium is 6.2 times of the coefficient of heat conductivity (0.023W/(m.k)) of air, so that the heat of a gyro motor product can be timely led out, the function of long-endurance and large tracking rate of the gyro is guaranteed, and (3) compared with normal-pressure (one atmosphere) air, 8 multiplied by 10 is filled in the gyro 4 After Pa helium, under standard conditions (one atmosphere pressure, 0 ℃), the density (0.1786 g/L) of the helium is only one seventh of the air density (1.29 g/L), so that the wind resistance of the gyro motor 1 during high-speed operation is smaller, and the heat generation of the outer rotor of the gyro motor 1 is effectively reduced.
The gyro inner ring assembly 2 comprises an inner ring frame 201 and gyro room upper and lower covers, and heat dissipation structures are arranged on the gyro motor 1 and the inner ring frame 201. Specifically, the heat dissipation structure between the gyro motor 1 and the inner ring frame 201 includes an annular heat conduction air gap 7 and an air guide hole 203; the gyro motor 1 is provided with a motor support shaft 101, the end part of the gyro motor 1 is provided with a motor end cover 202, the motor end cover 202 is provided with a motor via hole, the motor support shaft 101 penetrates through the motor via hole on the motor end cover 202, and an installation gap between the motor support shaft and the motor via hole forms an annular heat conduction air gap 7; the air holes 203 are disposed on the inner ring frame 201, preferably, the air holes 203 are disposed on the inner ring frame 201 around with central symmetry, and the number of the air holes 203 at each position on the inner ring frame 201 is 4, and the aperture sizes are different. Besides conducting heat by using the metal material of the gyroscope, the gyroscope is combined with a heat dissipation structure, so that the rapid heat conduction performance of the gyroscope is further optimized.
The outer rotor of the gyro motor 1 is of a spherical structure made of tungsten alloy, and the spherical structure of the gyro motor increases the outer surface area of the gyro motor and improves the heat dissipation performance.
The invention adopts compact spherical symmetrical design, combines the spherical structure of the gyro motor 1, combines the helium filling sealing and heat dissipation structure, and has the advantages of improving the heat dissipation performance of the small-sized rotor gyro, prolonging the service life of the gyro, along with strong environmental adaptability, high reliability, large tracking and measuring speed range and ensuring that all performance indexes of the small-sized rotor gyro meet the development requirements of a host machine.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (3)
1. The utility model provides a small-size rotor top with quick heat conduction structure, includes top shell (6), top shell (6) inside equipment has top motor (1), top inner ring subassembly (2), top outer ring subassembly (3), moment generator (4) and biax angle sensor (5), top inner ring subassembly (2) and top outer ring subassembly (3) mutually perpendicular alternately install in top shell (6), top motor (1) install in top inner ring subassembly (2) center inside with top motor (1) as center, moment generator (4) and biax angle sensor (5) are all installed to lower part, its characterized in that in top shell (6): the top motor (1), the moment generator (4), the double-shaft angle sensor (5) and the top shell (6) are of spherical symmetrical structures, the components inside the top shell (6) are vacuumized and filled with helium after being assembled, the top inner ring assembly (2) comprises an inner ring frame (201) and top and bottom covers of a top room, and heat dissipation structures are arranged on the top motor (1) and the inner ring frame (201);
the heat dissipation structure between the gyro motor (1) and the inner ring frame (201) comprises an annular heat conduction air gap (7) and an air guide hole (203); the top motor (1) is provided with a motor supporting shaft (101), the end part of the top motor (1) is provided with a motor end cover (202), the motor end cover (202) is provided with a motor via hole, the motor supporting shaft (101) passes through the motor via hole on the motor end cover (202) and an installation gap between the motor supporting shaft and the motor via hole forms an annular heat conduction air gap (7); the air guide holes (203) are arranged on the inner ring frame (201).
2. The small rotor gyroscope with rapid thermal conduction structure of claim 1, wherein: the inner ring frame (201) is provided with air holes (203) around in central symmetry, and the number of the air holes (203) at each position on the inner ring frame (201) is 4 and the aperture sizes are different.
3. The small rotor gyroscope with rapid thermal conduction structure of claim 1, wherein: the outer rotor of the gyro motor (1) is of a spherical structure made of tungsten alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911369913.XA CN111102971B (en) | 2019-12-26 | 2019-12-26 | Small rotor gyro with rapid heat conduction structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911369913.XA CN111102971B (en) | 2019-12-26 | 2019-12-26 | Small rotor gyro with rapid heat conduction structure |
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| Publication Number | Publication Date |
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| CN111102971A CN111102971A (en) | 2020-05-05 |
| CN111102971B true CN111102971B (en) | 2023-08-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911369913.XA Active CN111102971B (en) | 2019-12-26 | 2019-12-26 | Small rotor gyro with rapid heat conduction structure |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111964657A (en) * | 2020-07-15 | 2020-11-20 | 北京航天控制仪器研究所 | Double-layer vacuum heat-insulation structure for atomic gyroscope |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0333578A1 (en) * | 1988-03-16 | 1989-09-20 | Societe De Fabrication D'instruments De Mesure (S.F.I.M.) | Highly dynamic gyroscope |
| CN101219714A (en) * | 2007-12-26 | 2008-07-16 | 北京航空航天大学 | Double-frame magnetic suspension control moment gyro |
| CN104075700A (en) * | 2014-06-26 | 2014-10-01 | 北京控制工程研究所 | Small-size speed change control moment gyroscope |
| CN108036782A (en) * | 2017-12-13 | 2018-05-15 | 陕西宝成航空仪表有限责任公司 | Spherical symmetric gyro |
-
2019
- 2019-12-26 CN CN201911369913.XA patent/CN111102971B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0333578A1 (en) * | 1988-03-16 | 1989-09-20 | Societe De Fabrication D'instruments De Mesure (S.F.I.M.) | Highly dynamic gyroscope |
| CN101219714A (en) * | 2007-12-26 | 2008-07-16 | 北京航空航天大学 | Double-frame magnetic suspension control moment gyro |
| CN104075700A (en) * | 2014-06-26 | 2014-10-01 | 北京控制工程研究所 | Small-size speed change control moment gyroscope |
| CN108036782A (en) * | 2017-12-13 | 2018-05-15 | 陕西宝成航空仪表有限责任公司 | Spherical symmetric gyro |
Non-Patent Citations (1)
| Title |
|---|
| 刘春和 ; 霍文才 ; 刘训桂 ; 许水珠 ; .指北陀螺仪与永磁陀螺电机.中国惯性技术学报.1992,(01),全文. * |
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| CN111102971A (en) | 2020-05-05 |
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