CN112146641A - Four-axis high-precision optical fiber gyroscope combination for space - Google Patents
Four-axis high-precision optical fiber gyroscope combination for space Download PDFInfo
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- CN112146641A CN112146641A CN202011020191.XA CN202011020191A CN112146641A CN 112146641 A CN112146641 A CN 112146641A CN 202011020191 A CN202011020191 A CN 202011020191A CN 112146641 A CN112146641 A CN 112146641A
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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
- G01C19/58—Turn-sensitive devices without moving masses
- G01C19/64—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams
- G01C19/72—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams with counter-rotating light beams in a passive ring, e.g. fibre laser gyrometers
- G01C19/728—Assemblies for measuring along different axes, e.g. triads
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Abstract
The invention discloses a four-axis high-precision fiber optic gyroscope assembly for space, which comprises: the gyroscope comprises a base, a gyroscope support, side plates, a top cover and a circuit board; the first high-precision fiber-optic gyroscope is arranged on the gyroscope bracket; the second high-precision fiber-optic gyroscope is arranged on the gyroscope support; the third high-precision fiber-optic gyroscope is arranged on the gyroscope support; the fourth high-precision fiber-optic gyroscope is arranged on the gyroscope support; any two of the measuring shaft of the first high-precision optical fiber gyroscope, the measuring shaft of the second high-precision optical fiber gyroscope and the measuring shaft of the third high-precision optical fiber gyroscope are vertical to each other; the optical fiber gyroscope combination is composed of three orthogonal gyroscopes and one obliquely-installed gyroscope, wherein the failure of one optical fiber gyroscope does not cause the optical fiber gyroscope combination to be incapable of measuring three axial angular velocities of the satellite at the same time, so that the satellite can continuously realize attitude control, the fault tolerance of the optical fiber gyroscope combination is improved, and the four-axis optical fiber gyroscope combination can meet the requirements of long space life and high reliability.
Description
Technical Field
The invention relates to the field of inertial navigation, in particular to a four-axis high-precision fiber-optic gyroscope combination for space.
Background
The existing space application high-precision fiber-optic gyroscope combination has the defects that the size of a fiber-optic ring of the high-precision fiber-optic gyroscope is large, so that the formed four-axis high-precision fiber-optic gyroscope combination has large volume and heavy weight, and the gyroscope combination is designed mostly in a three-orthogonal mode. The mode has the characteristics of simplicity, practicability and convenience in installation. The existing triaxial high-precision fiber-optic gyroscope has the following defects: the optical fiber gyroscope combination is composed of three orthogonal gyroscopes, wherein faults of any gyroscope can cause that the combination cannot measure three axial angular velocities of the satellite at the same time, so that the satellite cannot realize attitude control; and secondly, the three-axis fiber-optic gyroscope combination cannot meet the requirements of long space life and high reliability.
Disclosure of Invention
The invention aims to provide a high-precision fiber-optic gyroscope combination suitable for an inertia sensitive system of a spacecraft, in particular to a fiber-optic gyroscope combination suitable for a satellite with large dynamic, high precision and long service life.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
further, the top assembly includes:
a top support;
the first high-precision fiber-optic gyroscope is mounted on the gyroscope support;
the second high-precision fiber-optic gyroscope is mounted on the gyroscope support;
the third high-precision fiber-optic gyroscope is arranged on the gyroscope support;
the fourth high-precision fiber-optic gyroscope is mounted on the gyroscope support;
any two of the measuring shaft of the first high-precision fiber-optic gyroscope, the measuring shaft of the second high-precision fiber-optic gyroscope and the measuring shaft of the third high-precision fiber-optic gyroscope are vertical to each other; the included angle between the measuring shaft of the first high-precision optical fiber gyroscope and the measuring shaft of the fourth high-precision optical fiber gyroscope is alpha, the included angle between the measuring shaft of the second high-precision optical fiber gyroscope and the measuring shaft of the fourth high-precision optical fiber gyroscope is beta, the included angle between the measuring shaft of the third high-precision optical fiber gyroscope and the measuring shaft of the fourth high-precision optical fiber gyroscope is gamma, and alpha, beta and gamma are all 54.74 degrees.
Further, the top combination further comprises:
the base is installed at the lower end of the gyro support, wherein the first high-precision optical fiber gyro, the second high-precision optical fiber gyro, the third high-precision optical fiber gyro and the fourth high-precision optical fiber gyro are installed on the base through the gyro support.
Further, the top combination further comprises:
a first side plate mounted on the base;
a second side plate mounted to the base;
a third side plate installed to the base;
a fourth side plate installed on the base
The first side plate, the second side plate, the third side plate, the fourth side plate and the base form an accommodating space with an open upper end.
Further, the top combination further comprises:
and the upper cover is arranged above the base and used for sealing the accommodating space.
Further, the top combination further comprises:
the lead skins are fixed through the protective supports and are respectively arranged above the devices with low total dose of radiation resistance on the circuit board in the first high-precision optical fiber gyro, the second high-precision optical fiber gyro, the third high-precision optical fiber gyro and the fourth high-precision optical fiber gyro.
Compared with the prior art, the invention has at least one of the following advantages:
the optical fiber gyroscope combination is composed of four orthogonal gyroscopes, wherein the failure of one optical fiber gyroscope does not cause the optical fiber gyroscope combination to be incapable of measuring three axial angular velocities of the satellite at the same time, so that the satellite can continuously realize attitude control, the fault tolerance of the optical fiber gyroscope combination is improved, and the four-axis optical fiber gyroscope combination can meet the requirements of long space life and high reliability.
Drawings
Fig. 1 is a schematic structural view of a four-axis high-precision fiber optic gyroscope assembly for a space according to an embodiment of the present invention with an upper cover and a part of a side plate removed;
FIG. 2 is a top view of the four-axis high-precision fiber optic gyroscope assembly for a space according to an embodiment of the present invention with the upper cover removed;
FIG. 3 is a schematic structural diagram of a spatial four-axis high-precision fiber optic gyroscope assembly according to an embodiment of the present invention;
fig. 4 is a schematic view of a gyro angle of a four-axis high-precision fiber-optic gyro combination for space in an embodiment of the present invention, wherein the first, second, third, and fourth high-precision fiber-optic gyros for space are referred to as gyros 1, 2, 3, and 4 for short.
Detailed Description
The present invention will be described in further detail with reference to the embodiments shown in fig. 1 to 4. The advantages and features of the present invention will become more apparent from the following description. It is to be noted that the drawings are in a very simplified form and are all used in a non-precise scale for the purpose of facilitating and distinctly aiding in the description of the embodiments of the present invention. To make the objects, features and advantages of the present invention comprehensible, reference is made to the accompanying drawings. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the implementation conditions of the present invention, so that the present invention has no technical significance, and any structural modification, ratio relationship change or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or field device 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 field device. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or field device that comprises the element.
Referring to fig. 1-4, the present embodiment provides a four-axis high-precision fiber optic gyroscope assembly for space use, the gyroscope assembly includes:
a top support 3;
a first high-precision fiber-optic gyroscope 2 (or called an X-axis fiber-optic gyroscope) mounted on the gyroscope support 3;
a second high-precision fiber-optic gyroscope 5 (or called Y-axis fiber-optic gyroscope) mounted on the gyroscope support 3;
a third high-precision fiber-optic gyroscope 13 (or called Z-axis fiber-optic gyroscope) mounted on the gyroscope support 3;
a fourth high-precision fiber-optic gyroscope 1 (or called S-axis fiber-optic gyroscope) mounted on the gyroscope support 3;
any two of the measuring axis of the first high-precision fiber-optic gyroscope 2, the measuring axis of the second high-precision fiber-optic gyroscope 5 and the measuring axis of the third high-precision fiber-optic gyroscope 13 are vertical to each other; the included angle between the measuring axis of the first high-precision optical fiber gyroscope 2 and the measuring axis of the fourth high-precision optical fiber gyroscope 1 is alpha, the included angle between the measuring axis of the second high-precision optical fiber gyroscope 5 and the measuring axis of the fourth high-precision optical fiber gyroscope 1 is beta, the included angle between the measuring axis of the third high-precision optical fiber gyroscope 13 and the measuring axis of the fourth high-precision optical fiber gyroscope 1 is gamma, and alpha, beta and gamma are all 54.74 degrees. The optical fiber gyroscope combination is composed of four orthogonal gyroscopes, wherein the failure of one optical fiber gyroscope cannot cause the optical fiber gyroscope combination to be incapable of measuring three axial angular velocities of the satellite at the same time, so that the satellite can continue to realize attitude control, the fault tolerance of the optical fiber gyroscope combination is improved, and the four-axis optical fiber gyroscope combination can meet the requirements of long space life and high reliability.
In this embodiment, the gyro combination further includes:
and the base 4 is used for being installed on the gyro bracket 3, wherein the first high-precision optical fiber gyro 2, the second high-precision optical fiber gyro 5, the third high-precision optical fiber gyro 13 and the fourth high-precision optical fiber gyro 1 are installed on the base 4 through the gyro bracket 3.
In this embodiment, the gyro combination further includes:
a first side plate 6 mounted to the base 4;
a second side plate 7 mounted on the base 4;
a third side plate 10 attached to the base 4;
a fourth side plate 15 mounted on the base 4
The first side plate, the second side plate, the third side plate, the fourth side plate and the base 4 form an accommodating space with an open upper end, and the first high-precision fiber-optic gyroscope 2, the second high-precision fiber-optic gyroscope 5 (or Y-axis fiber-optic gyroscope), the third high-precision fiber-optic gyroscope 13 and the fourth high-precision fiber-optic gyroscope 1 are all located in the accommodating space.
In this embodiment, the gyro combination further includes:
the upper cover is arranged above the base 4 and used for sealing the accommodating space to form a sealing structure, so that the installation accuracy of the four high-precision gyroscopes is guaranteed, the electromagnetism is shielded, a stable combined internal thermal environment is provided, and the gyroscopes are protected.
In this embodiment, the gyro combination further includes:
the protective bracket is used for fixing the lead sheet.
In this embodiment, the gyro combination further includes:
and the lead covers (8, 9, 11 and 12) are respectively arranged above the chip of the first high-precision optical fiber gyroscope 2, the chip of the second high-precision optical fiber gyroscope 5, the chip of the third high-precision optical fiber gyroscope 13 and the chip of the fourth high-precision optical fiber gyroscope 1, so that the radiation-sensitive chip is protected, the damage of space radiation to the chip is avoided, and the space environment adaptability and the service life of the optical fiber gyroscope combination are improved.
Four high accuracy fiber optic gyroscopes pass through the screw respectively and install on top support 3, and top installation face and top contact surface are all very smooth in order to guarantee the installation accuracy of top, and do benefit to the heat that produces the top and in time pass to top support 3 to reduce thermal pile up.
The gyro frame 3 is well installed, the gyro frame is horizontally installed on the base 4, a hexahedral closed space is formed by the gyro frame, the four side plates (6, 7, 10 and 15) and the upper cover 16, the aluminum alloy structural parts are directly overlapped and contacted between the side plates and the side plates, between the side plates and the base and between the side plates and the upper cover 16, the whole combination forms a complete shielding body without any gap, and the thermal stability and the magnetic stability inside the combination can be well guaranteed. The space between the structure and the circuit board is fully utilized, and the radiation resistance and the space environment adaptability of the component are enhanced by pasting a lead sheet with a certain thickness on the top structure of the component with weak radiation resistance.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (5)
1. A four-axis high-precision fiber optic gyroscope assembly for a space, the gyroscope assembly comprising:
a top support;
the first high-precision fiber-optic gyroscope is mounted on the gyroscope support;
the second high-precision fiber-optic gyroscope is mounted on the gyroscope support;
the third high-precision fiber-optic gyroscope is arranged on the gyroscope support;
the fourth high-precision fiber-optic gyroscope is mounted on the gyroscope support;
any two of the measuring shaft of the first high-precision fiber-optic gyroscope, the measuring shaft of the second high-precision fiber-optic gyroscope and the measuring shaft of the third high-precision fiber-optic gyroscope are vertical to each other; the included angle between the measuring shaft of the first high-precision optical fiber gyroscope and the measuring shaft of the fourth high-precision optical fiber gyroscope is alpha, the included angle between the measuring shaft of the second high-precision optical fiber gyroscope and the measuring shaft of the fourth high-precision optical fiber gyroscope is beta, the included angle between the measuring shaft of the third high-precision optical fiber gyroscope and the measuring shaft of the fourth high-precision optical fiber gyroscope is gamma, and alpha, beta and gamma are all 54.74 degrees.
2. A four-axis high precision fiber optic spatially gyroscope assembly as claimed in claim 1, further comprising:
the base is installed at the lower end of the gyro support, wherein the first high-precision optical fiber gyro, the second high-precision optical fiber gyro, the third high-precision optical fiber gyro and the fourth high-precision optical fiber gyro are installed on the base through the gyro support.
3. A four-axis high precision fiber optic spatially gyroscope assembly as claimed in claim 1 or 3, further comprising:
a first side plate mounted on the base;
a second side plate mounted to the base;
a third side plate installed to the base;
a fourth side plate installed on the base
The first side plate, the second side plate, the third side plate, the fourth side plate and the base form an accommodating space with an open upper end.
4. A four-axis high precision fiber optic spatially gyroscope assembly as claimed in claim 4, further comprising:
and the upper cover is arranged above the base and used for sealing the accommodating space.
5. A four-axis high precision fiber optic spatially gyroscope assembly as claimed in claim 1, further comprising:
the lead skins are fixed through the protective supports and are respectively arranged above the devices with low total dose of radiation resistance on the circuit board in the first high-precision optical fiber gyro, the second high-precision optical fiber gyro, the third high-precision optical fiber gyro and the fourth high-precision optical fiber gyro.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011020191.XA CN112146641A (en) | 2020-09-25 | 2020-09-25 | Four-axis high-precision optical fiber gyroscope combination for space |
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| CN202011020191.XA CN112146641A (en) | 2020-09-25 | 2020-09-25 | Four-axis high-precision optical fiber gyroscope combination for space |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123584A (en) * | 2022-06-27 | 2022-09-30 | 山东大学 | Structure and control dual-backup reaction flywheel system suitable for satellite S shaft and control method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123584A (en) * | 2022-06-27 | 2022-09-30 | 山东大学 | Structure and control dual-backup reaction flywheel system suitable for satellite S shaft and control method |
| CN115123584B (en) * | 2022-06-27 | 2024-06-07 | 山东大学 | Structure suitable for satellite S-axis and control dual-backup reaction flywheel system and control method |
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