Optical fiber gyroscope for satellites

Abstract

This invention relates to fiber optic gyroscopes, addressing the problem that existing satellite fiber optic gyroscopes struggle to simultaneously meet the comprehensive requirements of being lightweight, radiation-resistant, and possessing good temperature performance. This invention proposes a satellite fiber optic gyroscope, primarily comprising a cavity, three fiber optic ring modules, an optical module, and a circuit module. The cavity includes an outer bottom plate, an outer top frame, two mutually perpendicular and adjacent outer side plates, two mutually perpendicular and adjacent outer side frames, an outer top cover fastened to the outer top frame, two outer side covers fastened to the two outer side frames, an inner top plate, two mutually perpendicular and adjacent inner side plates, and an inner bottom cover. The outer bottom plate, two outer side plates, outer top cover, two outer side covers, inner top plate, and two inner side plates form an outer cavity; the inner top plate, two inner side plates, two outer side plates, and inner bottom cover form an inner cavity. One fiber optic ring module is disposed on the outer side wall of the inner top plate, and the other two fiber optic ring modules are respectively disposed on the outer side walls of the two inner side plates. The optical module and the circuit module are disposed within the inner cavity.

Description

Technical Field

[0001] This invention relates to a fiber optic gyroscope, specifically to a fiber optic gyroscope for satellites. Background Technology

[0002] Fiber optic gyroscopes are all-solid-state inertial measurement instruments based on the Sagnac effect. They possess advantages such as shock resistance, high sensitivity, long lifespan, large dynamic range, and short startup time, and have been widely used in marine, land, air, and space applications. In recent years, with the rapid development of the satellite industry, the requirements for fiber optic gyroscopes in terms of weight, size, radiation resistance, and temperature performance have become increasingly stringent.

[0003] Currently, fiber optic gyroscopes for satellites are typically designed with specific enhancements for a particular requirement, making it difficult to simultaneously meet comprehensive requirements such as being lightweight, radiation resistant, and having good temperature performance. Summary of the Invention

[0004] To address the challenge of existing fiber optic gyroscopes simultaneously meeting the comprehensive requirements of lightweight, miniaturization, radiation resistance, and good temperature performance, this invention proposes a satellite fiber optic gyroscope that effectively improves the radiation resistance and temperature performance of fiber optic gyroscopes. Furthermore, this fiber optic gyroscope boasts advantages such as small size, light weight, good mechanical properties, electromagnetic shielding performance, simple manufacturing method, high production efficiency, and low production cost.

[0005] To achieve the above objectives, the technical solution provided by this invention is:

[0006] A satellite fiber optic gyroscope includes a cavity, three fiber optic ring modules, an optical module, and a circuit module. The cavity is characterized by having an outer bottom plate, an outer top frame, two mutually perpendicular and adjacent outer side plates, two mutually perpendicular and adjacent outer side frames, an outer top cover fastened to the outer top frame, two outer side covers fastened to the two outer side frames, an inner top plate, two mutually perpendicular and adjacent inner side plates, and an inner bottom cover.

[0007] The outer bottom plate is provided with an insertion opening for the inner bottom cover; the inner bottom cover is fastened to the insertion opening on the outer bottom plate;

[0008] The outer bottom plate, inner bottom cover, outer top frame, outer top cover, two outer outer frames, two outer outer plates, and two outer outer covers constitute an outer hexahedron structure;

[0009] The inner bottom cover, two outer side plates, inner top plate, and two inner side plates constitute an inner hexahedron structure located within an outer hexahedron structure.

[0010] The outer bottom plate, two outer side plates, outer top frame, outer top cover, two outer side frames, two outer side covers, inner top plate, and two inner side plates form an outer cavity;

[0011] The inner top plate, two inner side plates, two outer side plates, and inner bottom cover form an inner cavity;

[0012] The three fiber optic ring modules are disposed inside the outer cavity, with one fiber optic ring module disposed on the outer wall of the inner top plate and the other two fiber optic ring modules disposed on the outer walls of the two inner side plates respectively.

[0013] The optical module and the circuit module are located inside the cavity.

[0014] The outer top cover, two outer side covers and inner bottom cover on the cavity have the same structure. They are all composed of an outer surface, a mounting surface and a boss located on the mounting surface. Their dimensions are adapted to the corresponding outer top frame, two outer side frames and inner bottom cover insertion opening on the outer bottom plate.

[0015] The compartmentalized structure design, with three fiber optic ring modules located in the outer cavity and the optical and circuit modules located in the inner cavity, effectively reduces the impact of heat generated by the optical and circuit modules on the fiber optic ring modules, ensuring that the three fiber optic ring modules are heated evenly within their installation space.

[0016] The optical and circuit modules within the cavity are connected via the inner top plate, two inner side plates, and two outer side plates.

[0017] The plate and inner bottom cover can provide further radiation protection.

[0018] Furthermore, three mutually orthogonally arranged mounting plates are provided on the outer walls of the inner top plate and the two inner side plates. Each mounting plate has a fiber optic ring module mounting boss, and the three fiber optic ring modules are respectively upside down.

[0019] Installed on the mounting boss of the fiber optic ring module;

[0020] The three mutually orthogonal mounting plates are all designed with weight-reducing and reinforcing rib structures;

[0021] The inner cavity is also equipped with a mounting platform for mounting optical modules and circuit modules.

[0022] The three orthogonally arranged mounting plates on the inner top plate and two inner side plates are all weight-reducing and reinforcing rib structures, and are integrated with the cavity design. While meeting the lightweight design requirements of the fiber optic gyroscope, they also provide sufficient strength and rigidity for the fiber optic ring module, ensuring the stability of the fiber optic gyroscope. The purpose of mounting the fiber optic ring module upside down on the fiber optic ring module mounting boss is to further enhance radiation protection. The mounting platform improves the installation stability of the optical module and the circuit module.

[0023] Furthermore, the mounting platform inside the inner cavity is provided with a first groove, a second groove, and a third groove;

[0024] The optical module includes a light source, a 1×3 coupler, a partition, a first support column, and a second support column. The light source is fixedly installed in groove I on the mounting platform inside the cavity. The 1×3 coupler is fixedly installed in groove II by adhesive. The light source pigtail is fused to one pigtail at one end of the 1×3 coupler. The partition is located between the first support column and the second support column. One end of the first support column is installed in the third groove. The second support column passes through the partition and is connected to the other end of the first support column.

[0025] The circuit module includes a circuit board mounting boss, a first circuit board, three photodetectors soldered on the first circuit board, and a second circuit board connected to the first circuit board via wires.

[0026] The first circuit board is fixedly installed on the other end of the second pillar, and the second circuit board is fixedly installed on the circuit board mounting boss; a rectangular notch from top to bottom is provided at the connection between one of the outer frames and one of the outer plates in the two outer frames, and a connector mounting groove is provided on the side wall of the rectangular notch;

[0027] A connector is installed on the connector mounting slot, and the connector communicates with the inner cavity through the connector mounting slot.

[0028] The partition design, positioned between the light source and the first circuit board, enhances the heat dissipation capability of the light source and the first circuit board through radiation to the partition. The connector placement makes full use of the cavity space and reduces the need for fiber optic gyroscopes.

[0029] The volume of the gyroscope.

[0030] Furthermore, the cavity, circuit board mounting boss, and partition are all made of aluminum; the first and second pillars are made of copper.

[0031] The purpose of using aluminum for the cavity, circuit board mounting boss, and partition is to reduce the overall weight of the fiber optic gyroscope, making it simpler and lighter; the use of copper as the support material can improve the heat dissipation capacity of the first circuit board and partition to the cavity through conduction.

[0032] Furthermore, the cavity, circuit board mounting boss, and partition are subjected to black anodizing treatment using the following steps:

[0033] S1. All parts constituting the cavity, circuit board mounting bosses, and partitions are subjected to black anodizing treatment.

[0034] S2. Perform the following removal of black anodizing treatment on all parts of the cavity, circuit board mounting bosses, and partitions that have already undergone black anodizing:

[0035] S2.1. The outer bottom plate, outer top frame, two outer side plates, two outer side frames, outer top cover, two outer side covers, and the outer side wall of the inner bottom cover of the cavity are all subjected to black anodizing treatment to maintain the original color of aluminum.

[0036] S2.2. Perform black anodizing treatment on the connection between the outer top frame and the outer top cover of the cavity to remove the black color of aluminum;

[0037] S2.3. Perform black anodizing treatment on the connection points between the two outer frames and the two outer covers on the cavity to remove the black color and keep the aluminum color.

[0038] S2.4. Perform black anodizing treatment on the connection between the outer bottom plate and the inner bottom cover of the cavity to remove the black color of aluminum;

[0039] S2.5, Remove the black anodizing agent from the connection points between the mounting bosses of the three fiber optic ring modules and the fiber optic ring modules.

[0040] Chemical treatment is used to preserve the natural color of aluminum;

[0041] S2.6. Perform black anodizing on the surface of the first groove on the inner cavity mounting platform corresponding to the light source.

[0042] Treatment to preserve the natural color of aluminum;

[0043] S2.7. Perform black anodizing treatment on the surfaces of the mounting bosses on the circuit board and the corresponding surfaces of the second circuit board to remove the black color of the aluminum.

[0044] The purpose of applying black anodizing to the entire cavity is to improve the heat dissipation capability of each module to the cavity through radiation. Then, the black anodizing treatment is applied to the connection points of the outer top frame and outer top cover, the two outer side frames and two outer side covers, and the outer bottom plate and inner bottom cover to maintain the natural color of aluminum. This is to achieve the overall conductivity continuity of the fiber optic gyroscope, reduce electromagnetic leakage, and improve the ability to resist external electromagnetic interference.

[0045] Furthermore, the outer bottom plate, outer top frame, two outer side plates, two outer side frames, outer top cover, two outer side covers, and the outer side wall of the inner bottom cover of the cavity are all coated with a thermal control coating with low absorptivity and high emissivity. This can effectively improve the heat dissipation capacity of the cavity.

[0046] Furthermore, the connections between the outer top frame and the outer top cover, the corresponding connections between the two outer side frames and the two outer side covers, and the connection between the outer bottom plate and the inner bottom cover are all snap-fit ​​overlapping structures. Using a snap-fit ​​overlapping structure facilitates the overall encapsulation of the cavity, reducing radiation leakage.

[0047] Furthermore, conductive sealant is applied to the connections between the outer top frame and the outer top cover, the corresponding connections between the two outer outer frames and the two outer outer covers, and the connection between the outer bottom plate and the inner bottom cover. This completes the overall sealing of the cavity and improves the radiation resistance of the fiber optic gyroscope.

[0048] Furthermore, the first circuit board is used to arrange components with low heat generation, and the second circuit board is used to arrange components with high heat generation.

[0049] The second circuit board has connecting bosses at both ends. The connecting bosses are copper-clad structures and are used to fix the second circuit board in the inner cavity.

[0050] Furthermore, the fiber optic ring module is equipped with a skeleton, fiber optic ring, fiber optic cover plate and device board. The lower end face of the device board is fixed with adhesive to a Y waveguide, a 2×2 coupler and a temperature sensor.

[0051] The frame and fiber optic cover are made of iron-nickel soft magnetic alloy, while the device board is made of magnesium-lithium alloy. The use of magnesium-lithium alloy for the device board further reduces the weight of the gyroscope.

[0052] The beneficial effects of this invention are as follows:

[0053] [1] The satellite fiber optic gyroscope of the present invention has good radiation resistance and temperature performance. At the same time, the fiber optic gyroscope is small in size, light in weight, and has good mechanical properties and electromagnetic shielding performance. The overall structure and manufacturing method of the gyroscope are simple, which can effectively improve production efficiency and reduce production costs.

[0054] [2] In this invention, the three fiber optic ring modules are respectively mounted on three mutually orthogonal mounting plates. The mounting plates are all designed with weight reduction and strengthening rib structure and are integrated with the cavity. While meeting the requirements of lightweighting, they also provide sufficient rigidity and strength for the fiber optic ring modules.

[0055] [3] In this invention, the fiber optic ring module and the optical module and circuit module located inside the cavity are designed as separate cavities, which can effectively reduce the impact of the heat generated by the optical module and circuit module on it and make it heated evenly.

[0056] [4] In this invention, the optical module and the circuit module are located inside the cavity. The inner top plate, two inner side plates, two outer side plates and the inner bottom cover of the cavity can provide further radiation protection.

[0057] [5] The cavity in this invention is made of aluminum. The connection between the outer top frame and the outer top cover, the connection between the two outer frames and the two outer covers, and the connection between the outer bottom plate and the inner bottom cover adopt a snap-fit ​​structure to complete the radiation protection of the entire fiber optic gyroscope and reduce radiation leakage.

[0058] [6] The fiber optic ring module in this invention is upside down on the inner cavity. The frame and fiber optic cover of the fiber optic ring module are made of iron-nickel soft magnetic alloy material, which can further protect the fiber optic ring from radiation. The adhesive glue on the lower end of the device board fixes the Y waveguide, 2×2 coupler and temperature sensor to further protect the components from radiation. The device board is designed as a magnesium-lithium alloy to further reduce the weight of the gyroscope.

[0059] [7] In this invention, the light source is directly mounted on the first groove of the mounting platform inside the cavity, and the surface of the first groove corresponding to the light source is subjected to black anodizing treatment to maintain the original color of aluminum, thereby improving the ability of the light source to dissipate heat to the cavity through conduction.

[0060] [8] In this invention, a partition is added between the light source and the first circuit board, and the surface of the partition is black anodized, which improves the ability of the light source and the first circuit board to dissipate heat to the partition through radiation. The second circuit board is designed with copper-plated mounting bosses and is directly installed in the inner cavity, which improves the ability of the second circuit board to dissipate heat to the cavity through conduction.

[0061] [9] In this invention, the first pillar and the second pillar are made of copper, which improves the ability of the first circuit board and the partition to dissipate heat to the cavity through conduction.

[0062]

[10] In this invention, by performing black anodizing on the inner and outer cavities of the cavity, the ability of the optical module and the circuit module to dissipate heat to the outer top cover, two outer side covers and inner bottom cover of the cavity through radiation is improved; the outer bottom plate, outer top frame, two outer side plates, two outer side frames, outer top cover, two outer side covers and inner bottom cover are coated with a low absorptivity, high emission thermal control coating, which improves the ability of the fiber optic gyroscope to dissipate heat to the outside through radiation and reduces the influence of external heat on the fiber optic gyroscope.

[0063]

[11] In this invention, the connection between the outer top frame and the outer top cover, the two outer side frames and the two outer side covers, and the outer bottom plate and the inner bottom cover on the cavity adopts a snap-fit ​​lap structure. The contact surfaces of the two maintain the original color of aluminum, and the connection is coated with conductive sealant to achieve the overall conductive continuity of the fiber optic gyroscope, reduce electromagnetic leakage, and improve the fiber optic gyroscope's ability to resist external electromagnetic interference.

[0064]

[12] In this invention, a partition is added between the light source and the first circuit board to reduce the electromagnetic interference between the light source and the first circuit board.

[0065]

[13] In this invention, a rectangular notch is provided at the connection between one of the outer frames and one of the outer plates in the two outer frames. A connector mounting slot is provided on the side wall of the rectangular notch. A connector is installed on the connector mounting slot. The connector communicates with the inner cavity through the connector mounting slot, making full use of the overall space of the cavity, reducing the volume of the fiber optic gyroscope, and realizing miniaturized design. Attached Figure Description

[0066] Figure 1 This is a schematic diagram of an embodiment of a fiber optic gyroscope for satellites according to the present invention;

[0067] Figure 2 This is a three-dimensional structural diagram of the cavity front in an embodiment of the present invention (the outer top cover and outer side cover are not shown).

[0068] Figure 3 This is a three-dimensional structural diagram of the bottom of the cavity in an embodiment of the present invention (the inner bottom cover is not shown).

[0069] Figure 4 This is a schematic cross-sectional view of the cavity in an embodiment of the present invention;

[0070] Figure 5 This is a schematic diagram of the front structure of the fiber optic ring module in an embodiment of the present invention;

[0071] Figure 6 This is a cross-sectional view of the fiber optic ring module installed upside down in an embodiment of the present invention;

[0072] Figure 7 This is a schematic diagram of the structure of the first and second pillars in an embodiment of the present invention;

[0073] Figure 8 This is a schematic diagram of the structure of the second circuit board in an embodiment of the present invention;

[0074] Figure 9 This is a schematic diagram of the front of the outer top cover, two outer side covers and the inner bottom cover in an embodiment of the present invention;

[0075] Figure 10 This is a schematic diagram of the structure of the outer top cover, two outer side covers, and the back of the inner bottom cover in an embodiment of the present invention;

[0076] Figure 11 This is a cross-sectional view of the connection between the outer top cover, two outer side covers, and inner bottom cover and the cavity in an embodiment of the present invention.

[0077] Reference numerals: 1-Cavity; 2-Outer bottom plate; 3-Outer top frame; 4-Outer side plate; 5-Outer side frame; 6-Outer top cover; 7-Outer side cover; 8-Inner top plate; 9-Inner side plate; 10-Inner bottom cover; 11-Fiber optic ring module; 12-Mounting plate; 13-Fiber optic ring module mounting boss; 14-Mounting platform; 15-First groove; 16-Second groove; 17-Third groove; 18-Light source; 19-1×3 coupler; 20-Partition plate; 21-First support column; 22-Second support column; 23-Circuit board mounting boss; 24-First circuit board; 2 5-Photodetector; 26-Second circuit board; 27-Connector; 28-Connector mounting slot; 29-Connecting boss; 30-Frame; 31-Fiber optic ring; 32-Fiber optic cover plate; 33-Device board; 34-Y waveguide; 35-2×2 coupler; 36-Temperature sensor; 37-Screw; 38-Threaded hole; 39-Equipment mounting boss; 40-Equipment mounting hole; 41-Cable routing hole; 42-First fiber routing hole; 43-Second fiber routing hole; 44-Device board connecting boss; 45-Outer surface; 46-Mounting surface; 47-Boss. Detailed Implementation

[0078] Depend on Figure 1 and Figure 2 As can be seen, the satellite fiber optic gyroscope of the present invention mainly includes a cavity 1, three fiber optic ring modules, an optical module, and a circuit module. The cavity 1 includes an outer bottom plate 2, an outer top frame 3, two mutually perpendicular and adjacent outer side plates 4, two mutually perpendicular and adjacent outer side frames 5, an outer top cover 6 fastened to the outer top frame 3, two outer side covers 7 fastened to the two outer side frames 5, an inner top plate 8, two mutually perpendicular and adjacent inner side plates 9, and an inner bottom cover 10; the outer bottom plate 2 is provided with an insertion opening for the inner bottom cover 10.

[0079] The outer bottom plate 2, inner bottom cover 10, outer top frame 3, outer top cover 6, two outer side frames 5, two outer side plates 4, and two outer side covers 7 constitute an outer hexahedron structure;

[0080] The inner bottom cover 10, the two outer side plates 4, the inner top plate 8, and the two inner side plates 9 constitute an inner hexahedron structure located within an outer hexahedron structure.

[0081] The outer bottom plate 2, two outer side plates 4, outer top frame 3, outer top cover 6, two outer side frames 5, two outer side covers 7, inner top plate 8, and two inner side plates 9 form an outer cavity; the inner top plate 8, two inner side plates 9, two outer side plates 4, and inner bottom cover 10 form an inner cavity.

[0082] Three fiber optic ring modules 11 are disposed within the outer cavity, with one of the fiber optic ring modules 11 disposed within the inner top plate 8.

[0083] On the outer side wall, the other two fiber optic ring modules 11 are respectively set on the outer side walls of the two inner side plates 9; the optical module and the circuit module are set inside the cavity.

[0084] The inner cavity and outer cavity of cavity 1 are an integral structure. Three mutually orthogonally arranged mounting plates 12 are provided on the outer walls of the inner top plate 8 and the two inner side plates 9 on the inner cavity of cavity 1. The mounting plates 12 are provided with fiber optic ring module mounting bosses 19. The inner cavity is provided with a mounting platform 14, and the mounting platform 14 is provided with a first groove 15, a second groove 16 and a third groove 17.

[0085] The three mutually orthogonal mounting plates 12 adopt a weight-reducing and reinforcing rib structure, forming an integrated structure with the inner and outer cavities.

[0086] Three fiber optic ring modules 11 are respectively mounted upside down on the fiber optic ring module mounting bosses 13 of three mutually orthogonal mounting plates 12 on the inner cavity.

[0087] The optical module includes a light source 18, a 1×3 coupler 19, a partition 20, a first support 21, and a second support 22. The light source 18 is fixedly installed in a first groove 15 on a mounting platform 14 within the inner cavity. The 1×3 coupler 19 is fixedly installed in a second groove 16 using adhesive. The pigtail of the light source 18 is fused to one pigtail at one end of the 1×3 coupler 19. The partition 20 is located between the first support 21 and the second support 22. One end of the first support 21 is installed in a third groove 17, and the second support 22 is connected to the other end of the first support 21 through a mounting hole on the partition 20. Figure 7 The first support 21 and the second support 22 shown have the same structure, are both made of copper, and are both composed of a bottom screw 37 and an upper threaded hole 38.

[0088] The circuit module includes a first circuit board 24, three photodetectors 25 soldered on the first circuit board 24, and a second circuit board 26 connected to the first circuit board 24 by wires. The first circuit board 24 is fixedly installed on the other end of the second support column 22, and the second circuit board 26 is fixedly installed on the circuit board mounting boss 23 provided on the mounting platform 14 in the inner cavity.

[0089] A rectangular notch running from top to bottom is provided at the connection between one of the two outer frames 5 and an outer panel 4, and a connector mounting groove 28 is provided on the side wall of the rectangular notch;

[0090] A connector 27 is installed on the connector mounting slot 28, and the connector 27 communicates with the inner cavity through the connector mounting slot 28.

[0091] like Figure 8 As shown, components with low heat generation are arranged on the first circuit board 24; components with high heat generation are arranged on the second circuit board 26. The second circuit board 26 has connecting bosses 29 at both ends, and the connecting bosses 29 have a copper-clad structure.

[0092] like Figure 9 and Figure 10 As shown, the outer top cover 6, the two outer outer covers 7, and the inner bottom cover 10 have the same structure, each consisting of an outer surface 45, a mounting surface 46, and a boss 47 located on the mounting surface 46, and their material is aluminum.

[0093] Its size is adapted to the corresponding outer top frame 3, two outer side frames 5 and inner bottom cover 10 on the outer bottom plate 2. The outer top cover 6 fastened to the outer top frame 3, the two outer side covers 7 fastened to the two outer side frames 5 and the inner bottom cover 10 fastened to the outer bottom plate 2 all adopt a fastening overlap structure for overall encapsulation of the cavity 1.

[0094] like Figure 3 and Figure 4 As shown, the cavity 1 also includes a device mounting boss 39 and a device mounting hole 40 for fixed connection with external devices, two upper cable routing holes 41, two first fiber routing holes 42, and two second fiber routing holes 43. The device mounting boss 39 and the device mounting hole 40 are the mechanical mounting interfaces for the fiber optic gyroscope.

[0095] The cavity 1 is made entirely of aluminum. The cavity 1, the circuit board mounting boss 23, and the partition 20 are subjected to black anodizing treatment using the following steps:

[0096] S1. All parts constituting cavity 1, circuit board mounting boss 23 and partition 20 are subjected to black anodizing treatment.

[0097] S2. Perform the following de-anodizing treatment on all parts of cavity 1, circuit board mounting bosses 23, and partitions 20 that have undergone black anodizing:

[0098] S2.1. Perform black anodizing treatment on the connection between the outer top frame 3 and the outer top cover 6 of the cavity 1 to maintain the original color of aluminum;

[0099] S2.2. Perform black anodizing treatment on the connection points of the two outer frames 5 and the two outer covers 7 on the cavity 1 to remove the black color and keep the aluminum color.

[0100] S2.3. Perform black anodizing treatment on the connection between the outer bottom plate 2 and the inner bottom cover 10 of the cavity 1 to maintain the original color of aluminum;

[0101] S2.4. Perform black anodizing treatment on the connection between the mounting boss 13 of the three fiber optic ring modules and the fiber optic ring module 11 to remove the black color of aluminum.

[0102] S2.5. Perform black anodizing treatment on the surface of the first groove 15 on the inner cavity mounting platform 14 corresponding to the light source 18 to maintain the original color of aluminum.

[0103] S2.6. Perform black anodizing treatment on the surfaces corresponding to the mounting boss 23 on the circuit board and the second circuit board 26 to remove the black color of aluminum.

[0104] Then, a low-absorption, high-emissivity thermal control coating is applied to the outer walls of the outer bottom plate 2, outer top frame 3, two outer side plates 4, two outer side frames 5, outer top cover 6, two outer side covers 7, and inner bottom cover 10 of cavity 1.

[0105] Conductive sealant is applied to the connection between the outer top frame 3 and the outer top cover 6, the corresponding connection between the two outer side frames 5 and the two outer side covers 7, and the connection between the outer bottom plate 2 and the inner bottom cover 10.

[0106] The first circuit board 24 is used to arrange components with low heat generation, and the second circuit board 26 is used to arrange components with high heat generation. The two ends of the second circuit board 26 are provided with connecting bosses 29, which are copper-clad structures and are used to fix the second circuit board 26 in the inner cavity.

[0107] like Figure 5 and Figure 6 As shown, the fiber optic ring module 11 mainly includes a frame 30, a fiber optic cover plate 32, a fiber optic ring 31, a device board 33, a Y-waveguide 34, a 2×2 coupler 35, and a temperature sensor 36. The fiber optic ring 31 is fixed to the frame 30 with adhesive; the frame 30 and the fiber optic cover plate 32 are fixedly connected by laser welding; the Y-waveguide 34, the 2×2 coupler 35, and the temperature sensor 36 are fixed to the lower end face of the device board 33 with adhesive; the lower end face of the device board 33 is also provided with device board connecting bosses 44 corresponding to the fiber optic ring module mounting bosses 13 of the mounting plate 12, and the device board 33 is fixed to the frame 30 with screws; the three fiber optic ring modules 11 are respectively mounted upside down on the fiber optic ring module mounting bosses 13 of the mounting plate 12 via the device board connecting bosses 44. The frame 30 and the fiber optic cover plate 32 are made of iron-nickel soft magnetic alloy, which completes the magnetic shielding of the fiber optic ring 31; the device board 33 is made of magnesium-lithium alloy, which can reduce the weight of the fiber optic gyroscope.

[0108] The specific manufacturing method of the fiber optic gyroscope in this invention is as follows:

[0109] Step 1: Fix the light source 18 in the first groove 15 on the mounting platform 14 inside the cavity 1; fix the 1×3 coupler 19 in the second groove 16 on the mounting platform 14 inside the cavity with adhesive; fused the pigtail of the light source 18 to one pigtail at one end of the 1×3 coupler 19.

[0110] Step 2: Install the first support column 21 into the third groove 17 on the mounting platform 14 through its screw 37 end; fix the partition plate 33 onto the first support column 21 through the screw 37 end of the second support column 22 and the threaded hole 38 of the first support column 21.

[0111] Step 3: Solder the three photodetectors 25 onto the first circuit board 24, and then fix the first circuit board 24 onto the second support 22 by screws and threaded holes 38 of the second support 22.

[0112] Step 4: Pass the three pigtails at the other end of the 1×3 coupler 19 and the three pigtails of the three photodetectors 25 through the wiring holes 41, the first fiber routing hole 42 and the second fiber routing hole 43 on the mounting platform 14 inside the cavity, respectively, and fused them with the two pigtails of the three fiber ring modules 11.

[0113] Step 5: Insert the Y-waveguide 34 wires and temperature sensor 35 wires of the three fiber optic ring modules 11 into the inner cavity through the wiring hole 41, the first fiber optic hole 42 and the second fiber optic hole 43 respectively. Then, install the fiber optic ring modules 11 upside down on the fiber optic ring module mounting boss 13 of the mounting plate 12 with screws.

[0114] Step 6: Connect the first circuit board 24 and the second circuit board 26 with wires, then install the second circuit board 26 on the circuit board mounting boss 23 with screws, and then solder the Y waveguide 34 wires of the three fiber optic ring modules 11, the temperature sensor 35 wires, and the light source 18 wires onto the second circuit board 26.

[0115] Step 7: Secure connector 27 to connector mounting groove 28 on cavity with screws, and solder connector 27 wires to second circuit board 26.

[0116] Step 8: Apply an appropriate amount of conductive sealant to the connection points of the outer top frame 3 and the outer top cover 6, the corresponding connection points of the two outer side frames 5 and the two outer side covers 7, and the connection points of the outer bottom plate 2 and the inner bottom cover 10 of the cavity 1. Then, fix the outer top frame 3 to the outer top cover 6, the two outer side frames 5 to the two outer side covers 7, and the outer bottom plate 2 to the inner bottom cover 10 with screws to complete the overall sealing of the cavity 1.

Claims

1. A fiber optic gyroscope for satellites, comprising a cavity (1), three fiber optic ring modules, an optical module, and a circuit module, characterized in that: The cavity (1) includes an outer bottom plate (2), an outer top frame (3), two mutually perpendicular and adjacent outer side plates (4), two mutually perpendicular and adjacent outer side frames (5), an outer top cover (6) fastened to the outer top frame (3), two outer side covers (7) fastened to the two outer side frames (5), an inner top plate (8), two mutually perpendicular and adjacent inner side plates (9), and an inner bottom cover (10). The outer bottom plate (2) is provided with an insertion opening for the inner bottom cover (10); the inner bottom cover (10) is fastened to the insertion opening on the outer bottom plate (2); The outer bottom plate (2), inner bottom cover (10), outer top frame (3), outer top cover (6), two outer side frames (5), two outer side plates (4), and two outer side covers (7) constitute an outer hexahedron structure; The inner bottom cover (10), two outer side plates (4), inner top plate (8), and two inner side plates (9) constitute an inner hexahedron structure located within an outer hexahedron structure; The outer bottom plate (2), two outer side plates (4), outer top frame (3), outer top cover (6), two outer side frames (5), two outer side covers (7), inner top plate (8), and two inner side plates (9) form an outer cavity; The inner top plate (8), two inner side plates (9), two outer side plates (4), and inner bottom cover (10) form an inner cavity; The three fiber optic ring modules (11) are disposed in the outer cavity, one of which is disposed on the outer side wall of the inner top plate (8), and the other two fiber optic ring modules (11) are disposed on the outer side walls of the two inner side plates (9). The optical module and the circuit module are located inside the cavity.

2. The fiber optic gyroscope for satellites according to claim 1, characterized in that: The inner top plate (8) and the two inner side plates (9) are provided with three mutually orthogonal mounting plates (12). The mounting plates (12) are provided with fiber optic ring module mounting bosses (13). The three fiber optic ring modules (11) are respectively upside down mounted on the fiber optic ring module mounting bosses (13). The three mutually orthogonal mounting plates (12) are all designed as weight-reducing and reinforcing rib structures; The inner cavity is also provided with a mounting platform (14) for mounting optical modules and circuit modules.

3. The fiber optic gyroscope for satellites according to claim 2, characterized in that: The mounting platform (14) inside the cavity is provided with a first groove (15), a second groove (16) and a third groove (17). The optical module includes a light source (18), a 1×3 coupler (19), a partition (20), a first support (21), and a second support (22). The light source (18) is fixedly installed in the first groove (15) on the mounting platform (14) inside the cavity. The 1×3 coupler (19) is fixedly installed in the second groove (16) by adhesive. The pigtail of the light source (18) is fused to one pigtail at one end of the 1×3 coupler (19). The partition (20) is located between the first support (21) and the second support (22). One end of the first support (21) is installed in the third groove (17). The second support (22) passes through the partition (20) and is connected to the other end of the first support (21). The circuit module includes a first circuit board (24), three photodetectors (25) soldered on the first circuit board (24), and a second circuit board (26) connected to the first circuit board (24) by wires; The first circuit board (24) is fixedly mounted on the other end of the second support (22), and the second circuit board (26) is fixedly mounted on the circuit board mounting boss (23) provided on the mounting platform (14) in the inner cavity; A rectangular notch running from top to bottom is provided at the connection between one of the two outer frames (5) and an outer plate (4), and a connector mounting groove (28) is provided on the side wall of the rectangular notch. A connector (27) is installed on the connector mounting slot (28), and the connector (27) communicates with the inner cavity through the connector mounting slot (28).

4. A fiber optic gyroscope for satellites according to claim 3, characterized in that: The cavity (1), the circuit board mounting boss (23) and the partition (20) are all made of aluminum. The first pillar (21) and the second pillar (22) are copper pillars.

5. A fiber optic gyroscope for satellites according to claim 4, characterized in that, The cavity (1), circuit board mounting boss (23), and partition (20) are subjected to black anodizing treatment using the following steps: S1. All parts constituting the cavity (1), the circuit board mounting boss (23), and the partition (20) are subjected to black anodizing treatment; S2. Perform the following de-anodizing treatment on each part of the cavity (1), the circuit board mounting boss (23), and the partition (20) that have undergone black anodizing: S2.

1. The outer bottom plate (2), outer top frame (3), two outer side plates (4), two outer side frames (5), outer top cover (6), two outer side covers (7), and inner bottom cover (10) of the cavity (1) are all subjected to black anodizing treatment to maintain the original color of aluminum. S2.

2. Perform black anodizing treatment on the connection between the outer top frame (3) and the outer top cover (6) of the cavity (1) to maintain the original color of aluminum; S2.

3. Perform black anodizing treatment on the connection points of the two outer frames (5) and the two outer covers (7) on the cavity (1) to maintain the original color of aluminum; S2.

4. Perform black anodizing treatment on the connection between the outer bottom plate (2) and the inner bottom cover (10) of the cavity (1) to maintain the original color of aluminum; S2.

5. Perform black anodizing treatment on the connection between the three fiber optic ring module mounting bosses (13) and the fiber optic ring module (11) to maintain the original aluminum color. S2.

6. Perform black anodizing treatment on the surface of the first groove (15) on the inner cavity mounting platform (14) corresponding to the light source (18) to maintain the original color of aluminum. S2.7 Remove the black residue from the surfaces corresponding to the mounting boss (23) on the circuit board and the second circuit board (26). The aluminum is anodized to maintain its original color.

6. A fiber optic gyroscope for satellites according to claim 5, characterized in that: The outer bottom plate (2), outer top frame (3), two outer side plates (4), two outer side frames (5), outer top cover (6), two outer side covers (7), and inner bottom cover (10) of the cavity (1) are all coated with a thermal control coating with low absorptivity and high emissivity.

7. A fiber optic gyroscope for satellites according to claim 6, characterized in that: The connection between the outer top frame (3) and the outer top cover (6), the connection between the two outer frames (5) and the two outer covers (7), and the connection between the outer bottom plate (2) and the inner bottom cover (10) are all snap-fit ​​overlapping structures.

8. A fiber optic gyroscope for satellites according to claim 7, characterized in that: Conductive sealant is applied to the connection between the outer top frame (3) and the outer top cover (6), the connection between the two outer frames (5) and the two outer covers (7), and the connection between the outer bottom plate (2) and the inner bottom cover (10).

9. A fiber optic gyroscope for satellites according to claim 8, characterized in that: The first circuit board (24) is used to arrange components with low heat generation, and the second circuit board (26) is used to arrange components with high heat generation; The second circuit board (26) has connecting bosses (29) at both ends. The connecting bosses (29) are copper-clad structures and are used to fix the second circuit board (26) in the inner cavity.

10. A fiber optic gyroscope for satellites according to claim 9, characterized in that: The fiber optic ring module (11) is provided with a skeleton (30), a fiber optic ring (31), a fiber optic cover plate (32) and a device board (33). The lower end face of the device board (33) is fixed with adhesive to a Y waveguide (34), a 2×2 coupler (35) and a temperature sensor (36). The skeleton (30) and the fiber cover plate (32) are made of iron-nickel soft magnetic alloy, and the device plate (33) is made of magnesium-lithium alloy.

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