Optical fiber inertial navigation system

Abstract

The invention relates to an inertial navigation system, in particular to an optical fiber inertial navigation system. The aircraft power supply switching device comprises a main framework, an accelerometer bracket, three fiber-optic gyroscopes, three accelerometers, a system board and a power supply board, wherein three mutually orthogonally arranged fiber-optic gyroscope mounting surfaces are arranged in the main framework; the accelerometer bracket is fixed in the main framework; the three fiber-optic gyroscopes are mounted on the fiber-optic gyroscope mounting surface; the three accelerometers are arranged in a mutually orthogonal mode, and the accelerometers are all arranged on the accelerometer support. The system board is mounted at a system board mounting boss arranged in the main framework; and the power panel is mounted on a power panel mounting surface arranged in the main framework. The optical fiber inertial navigation system comprises a main framework, an accelerometer support, an optical fiber gyroscope, an accelerometer, a system board and a power board. The optical fiber inertial navigation system is compact in structure, high in space utilization rate, light in weight, small in size and good in heat dissipation and shock resistance.

Description

Technical Field

[0001] The invention relates to an inertial navigation system, in particular to an optical fiber inertial navigation system. Background Art

[0002] The fiber-optic inertial navigation system is an inertial reference system that measures the acceleration and angular velocity of the carrier through the accelerometer and fiber-optic gyroscope, and then integrates it over time to obtain the carrier's current speed, direction, and position. Inertial navigation systems are currently mainly used in many vehicles such as aircraft, underwater submersibles, space shuttles, ships, and missiles. In recent years, with the development of technology, the performance indicators, cost, reliability, and size of fiber-optic inertial navigation have become increasingly demanding.

[0003] The existing fiber optic inertial navigation system structures on the market usually have problems such as unreasonable internal device layout, heavy weight, low space utilization, difficult structural parts processing, poor heat dissipation performance, and low seismic resistance. Summary of the invention

[0004] In view of the above-mentioned shortcomings of the prior art, an object of the present invention is to provide a fiber optic inertial navigation system with compact structure, high space utilization, light weight, small size, and good heat dissipation and shock resistance.

[0005] To achieve the above-mentioned and other related purposes, the present invention provides a fiber optic inertial navigation system, comprising:

[0006] A main frame, inside which are provided three fiber optic gyroscope mounting surfaces arranged orthogonally to each other;

[0007] An accelerometer bracket, which is fixed inside the main frame;

[0008] Three fiber optic gyroscopes, which are mounted on the fiber optic gyroscope mounting surface;

[0009] Three accelerometers, the three accelerometers are arranged orthogonally to each other, and the accelerometers are all arranged on the accelerometer bracket;

[0010] A system board, which is installed on a system board installation boss provided in the main frame;

[0011] A power board is installed on the power board installation surface provided in the main frame.

[0012] In one embodiment of the present invention, the three fiber optic gyroscopes are respectively an X-axis fiber optic gyroscope, a Y-axis fiber optic gyroscope, and a Z-axis fiber optic gyroscope, and the X-axis fiber optic gyroscope, the Y-axis fiber optic gyroscope, and the Z-axis fiber optic gyroscope are separated from each other by a baffle, the X-axis fiber optic gyroscope and the Y-axis fiber optic gyroscope are arranged on the upper side of the main frame, and the Z-axis fiber optic gyroscope is arranged at the bottom of the main frame; the accelerometer bracket and the Y-axis fiber optic gyroscope are arranged on the same side of the main frame, and the accelerometer bracket and the Y-axis fiber optic gyroscope are separated by a baffle.

[0013] In one embodiment of the present invention, the system board mounting bosses are disposed on the top and bottom of a main frame on which the accelerometer bracket is mounted.

[0014] In one embodiment of the present invention, the power board mounting surface is disposed on the inner side of a main frame on which the accelerometer bracket is mounted, and is located on the inner side of the system board mounting boss.

[0015] In one embodiment of the present invention, the accelerometer bracket is provided with an X-axis accelerometer, a Y-axis accelerometer, and a Z-axis accelerometer that are arranged orthogonally to each other.

[0016] In one embodiment of the present invention, it further includes:

[0017] Side panels, which are arranged on both sides of the main frame and are used to cover the outer sides of the fiber optic gyroscope, accelerometer, system board, and power board;

[0018] The weight-reducing groove is arranged on the outer side of the main frame.

[0019] In one embodiment of the present invention, it further includes:

[0020] An external 15-core connector installation groove is embedded in the front face of the main frame so that the connector is located inside the end face of the main frame;

[0021] The external 25-core connector installation groove is embedded in the front face of the main frame so that the connector is located on the inner side of the end face of the main frame.

[0022] In one embodiment of the present invention, four corners of the bottom of the main frame are provided with mounting holes, the mounting holes do not exceed the four sides of the main frame, and the mounting holes are used to fix the inertial navigation system.

[0023] In one embodiment of the present invention, it further includes:

[0024] A reinforcing rib, which is arranged at the bottom of the main frame;

[0025] A first wiring groove of the main frame, which is arranged inside the main frame;

[0026] The second wiring groove of the main frame is arranged inside the main frame.

[0027] In one embodiment of the present invention, it further includes:

[0028] Threaded blind holes are arranged at multiple mounting surfaces of the main frame and are used to fix cables.

[0029] As described above, the fiber optic inertial navigation system of the present invention has the following beneficial effects:

[0030] (1) The fiber optic inertial navigation system of the present invention comprises a main frame, an accelerometer bracket, a fiber optic gyroscope, an accelerometer, a system board, and a power board. The present invention has a compact structure, high space utilization, light weight, small size, and good heat dissipation and shock resistance.

[0031] (2) The installation hole of the fiber optic inertial navigation system of the present invention is arranged on the inner side of the main frame, so as to fully utilize the space above the installation hole.

[0032] (3) The fiber optic inertial navigation system of the present invention adopts a precise main frame weight reduction design so that the center of mass of the entire system is located directly below the centroid, which can greatly improve the seismic performance of the system.

[0033] (4) The fiber optic inertial navigation system of the present invention disperses the heat generated by the system power supply to the entire main frame, and then directly dissipates the heat to the external environment through the side walls of the main frame, thereby greatly improving the heat dissipation capacity of the system.

[0034] (5) The fiber optic inertial navigation system of the present invention has a compact size. Based on the use of a 98 mm diameter fiber optic gyroscope, its overall size is only 110 mm×154 mm×154 mm. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 A schematic diagram of the appearance and structure of a fiber optic inertial navigation system provided in an embodiment of the present application.

[0036] Figure 2 A schematic diagram of a fiber optic inertial navigation system provided in an embodiment of the present application with the side panel removed, in the direction of A.

[0037] Figure 3 A schematic diagram of a fiber optic inertial navigation system provided in an embodiment of the present application with the side panel removed, in the direction of B.

[0038] Figure 4 A schematic diagram of a fiber optic inertial navigation system provided in an embodiment of the present application, with the side panels and system board removed, in the direction of B.

[0039] Figure 5 A schematic diagram of the C-direction structure of the main skeleton of a fiber-optic inertial navigation system provided in an embodiment of the present application.

[0040] Figure 6 A schematic diagram of the D-axis structure of the main skeleton of a fiber-optic inertial navigation system provided in an embodiment of the present application.

[0041] Figure 7 A schematic diagram of the structure of an accelerometer bracket of a fiber optic inertial navigation system provided in an embodiment of the present application.

[0042] Component number description:

[0043] 1-Main skeleton

[0044] 11-Weight reduction groove

[0045] 12-External 15-core connector installation groove

[0046] 13-External 25-core connector installation groove

[0047] 14-X-axis fiber optic gyro mounting surface

[0048] 15-Y-axis fiber optic gyro mounting surface

[0049] 16-Z-axis fiber optic gyro mounting surface

[0050] 17-Power board installation surface

[0051] 18-Add table bracket installation surface

[0052] 19-System board mounting boss

[0053] 1A-Main frame first wiring groove

[0054] 1B-Second wiring groove of the main frame

[0055] 1C - Mounting hole

[0056] 1D-Cable fixing hole

[0057] 1E-Reinforcement Ribs

[0058] 2-Side panels

[0059] 31-X axis fiber optic gyroscope

[0060] 32-Y-axis fiber optic gyroscope

[0061] 33-Z-axis fiber optic gyroscope

[0062] 41-X axis plus table

[0063] 42-Y axis plus table

[0064] 43-Z axis plus table

[0065] 5-Accelerometer bracket

[0066] 51-X-axis accelerometer mounting surface

[0067] 52-Y-axis accelerometer mounting surface

[0068] 53-Z-axis accelerometer mounting surface

[0069] 6-System board

[0070] 61-Fiber Optic Gyroscope Connector

[0071] 62-Power connector

[0072] 63-Accelerometer connector

[0073] 64-External plug-in

[0074] 7-Power board

[0075] 8-15 core connector

[0076] 9-25 core connector DETAILED DESCRIPTION

[0077] The following describes the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0078] It should be noted that the illustrations provided in the following embodiments are only used to illustrate the basic concept of the present invention in a schematic manner, and thus the illustrations only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0079] Terms such as first or second can be used to describe various components, but these components are not limited by the above terms. The above terms are used to distinguish one component from another component, for example, without departing from the scope of the concept according to the present disclosure, a first component can be referred to as a second component, and similarly, a second component can be referred to as a first component.

[0080] In addition, "connected / coupled" means that one component is directly electrically coupled to another component or is indirectly electrically coupled through another component. The singular form may include the plural form unless explicitly stated in the sentence. In addition, "include / comprise" or "includes / comprises" used in this specification indicates that one or more components, steps, operations, and elements exist or have been added. The specific structural or functional descriptions of the examples of the implementation of the concepts disclosed in this specification are only illustrated to describe the examples of the implementation of the concepts, and the examples of the implementation of the concepts can be implemented in various forms, but these descriptions are not limited to the examples of the implementation described in this specification.

[0081] According to the concept, various modifications and changes can be applied to the examples of the embodiments, so that the examples of the embodiments will be illustrated in the drawings and described in the specification. However, the examples of the embodiments according to the concept are not limited to the specific embodiments, but include all changes, equivalents or replacements included in the spirit and technical scope of the present disclosure.

[0082] It should be understood that when an element is described as being "coupled" or "connected" to another element, the element may be directly coupled or directly connected to the other element, or may be coupled or connected to the other element through a third element. Conversely, it should be understood that when an element is referred to as being "directly coupled to" or "directly coupled to" another element, no other element is placed between them. Other expressions describing the relationship between components (i.e., "between" and "directly between" or "adjacent to" and "directly adjacent to") need to be interpreted in the same manner.

[0083] The terms used in this specification are only used to describe specific examples of the embodiments and are not intended to limit the present disclosure. If there is no clear opposite meaning in the context, the singular form may include the plural form. In this specification, it should be understood that the term "including" or "having" indicates the presence of the features, quantities, steps, operations, components, parts or combinations thereof described in the specification, but the possibility of the presence or addition of one or more other features, quantities, steps, operations, components, parts or combinations thereof cannot be precluded.

[0084] If there is no contrary definition, all terms (including technical terms or scientific terms) used herein have the same meaning as those generally understood by ordinary technicians in the field. If the terms defined in the commonly used dictionary are not clearly defined in this specification, they should be interpreted as having the same meaning as in the context of the relevant technology, and not interpreted as ideal or overly formal meanings.

[0085] Descriptions of well-known components and processing techniques may be omitted so as not to unnecessarily obscure the embodiments of the disclosure.

[0086] Throughout the specification, the same reference numerals refer to the same elements. Thus, even if a reference numeral is not mentioned or described with reference to one figure, it may be mentioned or described with reference to another figure. Furthermore, even if a reference numeral is not shown in one figure, it may be mentioned or described with reference to another figure.

[0087] In addition, the logic level of the signal may be different or opposite to the described logic level. For example, a signal described as having a logic "high" level may alternatively have a logic "low" level, and a signal described as having a logic "low" level may alternatively have a logic "high" level.

[0088] The following will describe the various embodiments of the present disclosure in detail with reference to the accompanying drawings. However, it will be appreciated by those skilled in the art that in the various embodiments of the present disclosure, many technical details are provided in order to enable the reader to better understand the present disclosure. However, even without these technical details and various changes and modifications based on the following embodiments, the technical solutions claimed in the present disclosure can be implemented.

[0089] See also Figure 1 to Figure 7 , Figure 1 A schematic diagram of the appearance and structure of a fiber optic inertial navigation system provided in an embodiment of the present application. Figure 2 A schematic diagram of a fiber optic inertial navigation system provided in an embodiment of the present application with the side panel removed, in the direction of A. Figure 3 A schematic diagram of a fiber optic inertial navigation system provided in an embodiment of the present application with the side panel removed, in the direction of B. Figure 4 A schematic diagram of a fiber optic inertial navigation system provided in an embodiment of the present application, with the side panels and system board removed, in the direction of B. Figure 5 A schematic diagram of the C-direction structure of the main skeleton of a fiber-optic inertial navigation system provided in an embodiment of the present application. Figure 6 A schematic diagram of the D-axis structure of the main skeleton of a fiber-optic inertial navigation system provided in an embodiment of the present application. Figure 7 A schematic diagram of the accelerometer bracket structure of a fiber optic inertial navigation system provided in an embodiment of the present application. The present invention provides a fiber optic inertial navigation system, including a main skeleton 1, an accelerometer bracket 5, three fiber optic gyroscopes, three accelerometers, a system board 6, and a power board 7. The main skeleton 1 is provided with three mutually orthogonally arranged fiber optic gyroscope mounting surfaces; the accelerometer bracket 5 is fixed to the inside of the main skeleton 1; the three fiber optic gyroscopes are mounted on the fiber optic gyroscope mounting surfaces; the three accelerometers are arranged orthogonally to each other, and the accelerometers are all arranged on the accelerometer bracket 5; the system board 6 is mounted on the system board mounting boss 19 provided in the main skeleton 1; the power board 7 is mounted on the power board mounting surface 17 provided in the main skeleton 1.

[0090] Specifically, three fiber optic gyroscopes are directly mounted on the main frame 1. Compared with the traditional structure in which the fiber optic gyroscope is first mounted on the IMU bracket and then the IMU bracket is fixed on the base plate, the structure is simpler and the anti-seismic effect is better.

[0091] Specifically, the three fiber optic gyroscopes are respectively an X-axis fiber optic gyroscope 31, a Y-axis fiber optic gyroscope 32, and a Z-axis fiber optic gyroscope 33, and the X-axis fiber optic gyroscope 31, the Y-axis fiber optic gyroscope 32, and the Z-axis fiber optic gyroscope 33 are separated from each other by a baffle. The X-axis fiber optic gyroscope 31 and the Y-axis fiber optic gyroscope 32 are arranged on the upper side of the main skeleton 1, and the Z-axis fiber optic gyroscope 33 is arranged at the bottom of the main skeleton 1; the accelerometer bracket 5 and the Y-axis fiber optic gyroscope 32 are arranged on the same side of the main skeleton 1, and the accelerometer bracket 5 and the Y-axis fiber optic gyroscope 32 are separated by a baffle.

[0092] Specifically, since the main frame 1 is provided with the system board mounting boss 19 , the system board mounting bracket is omitted, thus saving costs.

[0093] Specifically, since the main frame 1 is provided with a power board mounting surface 17, the power board mounting bracket is omitted, and the power supply with a larger heat generation is directly in contact with the main frame 1 made of aluminum material, which greatly increases the heat dissipation capacity of the system.

[0094] In some embodiments of the present invention, the system board mounting bosses 19 are disposed at the top and bottom of the main frame 1 on which the accelerometer bracket 5 is mounted.

[0095] In some embodiments of the present invention, the power board mounting surface 17 is disposed on the inner side of the main frame 1 on which the accelerometer bracket 5 is mounted, and is located on the inner side of the system board mounting boss 19 .

[0096] In some embodiments of the present invention, the accelerometer bracket 5 is provided with an X-axis accelerometer 41, a Y-axis accelerometer 42, and a Z-axis accelerometer 43 which are arranged orthogonally to each other.

[0097] In some embodiments of the present invention, the fiber optic inertial navigation system further comprises:

[0098] The side panels 2 are arranged on both sides of the main frame 1 and are used to cover the outer sides of the fiber optic gyroscope, the accelerometer, the system board 6 and the power board 7.

[0099] Specifically, the two side panels 2 have the same structure, which reduces the difficulty of processing. The two side panels 2 are used to provide protection for the entire inertial navigation system.

[0100] Specifically, the two side panels 2 do not bear weight due to reasonable structural design, have a maximum thickness of only 2 mm, and are provided with large-area 1 mm deep weight-reducing grooves, which further reduces the overall mass of the fiber-optic inertial navigation system.

[0101] The weight-reducing grooves 11 are arranged on the outer side of the main frame 1 . Specifically, a plurality of weight-reducing grooves 11 are arranged on the non-open end of the main frame 1 .

[0102] The external 15-core connector installation groove 12 is embedded in the front side of the main frame 1 so that the connector is located on the inner side of the end surface of the main frame 1.

[0103] The external 25-core connector installation groove 13 is embedded in the front surface of the main frame 1 so that the connector is located on the inner side of the end surface of the main frame 1.

[0104] Since the front side of the main frame 1 is provided with an embedded external 15-core connector installation groove 12 and an external 25-core connector installation groove 13, the connectors are located on the inner side of the end surface of the main frame 1, which increases safety and reliability.

[0105] The reinforcing rib 1E is arranged at the bottom of the main frame 1 to increase the overall strength.

[0106] The first wiring groove 1A of the main frame is arranged inside the main frame 1.

[0107] The second wiring groove 1B of the main frame is arranged inside the main frame 1.

[0108] Specifically, the provision of the first wiring groove 1A of the main frame and the second wiring groove 1B of the main frame is conducive to cable arrangement.

[0109] Threaded blind holes are provided at multiple mounting surfaces of the main frame 1 and are used to fix cables.

[0110] In some embodiments of the present invention, mounting holes 1C are provided at the four corners of the bottom of the main skeleton 1. The mounting holes 1C do not exceed the four sides of the main skeleton 1. The mounting holes 1C are used to fix the inertial navigation system. Specifically, the space directly above the mounting holes 1C can be fully utilized to increase space utilization.

[0111] In a first embodiment of the present invention, the present invention provides a fiber optic inertial navigation system suitable for a 98 gyroscope, comprising:

[0112] Please see attached Figures 5-6 In the embodiment of the present invention, the structure of the main skeleton 1 is greatly optimized compared to the complex structure of IMU bracket + base + multiple mounting brackets + housing + top cover used in the traditional inertial navigation system.

[0113] The structure of a traditional inertial navigation system requires additional power board brackets and system board brackets to fix the power board and the system board, and introduces too many structural parts, which makes the installation complicated, reduces the reliability, and has poor heat dissipation effect of the power supply. The main skeleton of the present invention optimizes the complex structure of IMU bracket + base + multiple mounting brackets + outer shell + top cover used in traditional inertial navigation systems, improves the IMU bracket, base and multiple mounting brackets into a single main skeleton structure, and improves the outer shell and top cover into two side panels 2 of the same structure.

[0114] A power board mounting surface 17 is provided on the main frame 1 to fix the power board and enable the power supply to fit the main frame 1 for heat dissipation. A system board mounting boss 19 is provided on the main frame 1 to fix the system board 6, so that the structure has a high degree of integration.

[0115] The traditional inertial navigation structure sets the connector installation surface on the surface of the inertial navigation shell, so that the connector protrudes from the shell, which not only takes up space but is also easy to be damaged; the front side of the main frame 1 of the present invention is provided with an embedded external 15-core connector installation groove 12 and an external 25-core connector installation groove 13, so that the connector is completely on the inner side of the outer end surface of the main frame 1, thereby solving the above-mentioned problem.

[0116] The side panels 2 are provided with large-area weight-reducing grooves 11 and countersunk holes for fixing to the main frame 1 .

[0117] In the second embodiment of the present invention, based on the first embodiment, this example provides a forming method of a fiber optic inertial navigation system suitable for a 98 gyroscope, and the specific steps are as follows:

[0118] Step 1: Install the accelerometer. The specific steps are as follows:

[0119] The X-axis accelerometer, Y-axis accelerometer, and Z-axis accelerometer are respectively fixed to the three mutually orthogonal X-axis accelerometer mounting surfaces 51, Y-axis accelerometer mounting surfaces 52, and Z-axis accelerometer mounting surfaces 53 of the accelerometer bracket 5 with screws; the accelerometer bracket 5 is fixed to the meter bracket mounting surface 18 of the main frame 1 with screws.

[0120] Step 2: Install the fiber optic gyroscope. The specific method is as follows:

[0121] The X-axis fiber optic gyroscope 31, the Y-axis fiber optic gyroscope 32, and the Z-axis fiber optic gyroscope 33 are respectively fixed to the three mutually orthogonal X-axis fiber optic gyroscope mounting surfaces 14, Y-axis fiber optic gyroscope mounting surfaces 15, and Z-axis fiber optic gyroscope mounting surfaces 16 of the main frame 1 with screws.

[0122] Step 3: Install the power board. The specific steps are as follows:

[0123] Fix the four copper studs to the four threaded holes on the power board mounting surface 17 of the main frame 1, evenly apply a thin layer of thermal conductive silicone grease on the power supply on the power board, and fix it to the four copper studs with screws, so that the power supply can fully fit with the power board mounting surface 17 of the main frame 1.

[0124] Step 4: Install the 15-core connector 8 and the 25-core connector 9. The specific method is as follows:

[0125] The 15-core connector 8 and the 25-core connector 9 are respectively fixed to the 15-core connector mounting groove and the 25-core connector mounting groove 13 provided in the main frame 1 by screws.

[0126] Step 5: Cable connection. The specific method is as follows:

[0127] The Y-axis fiber optic gyroscope cable passes through the first routing groove 1A of the main frame 1 and the second routing groove 1B of the main frame 1 in sequence, and then is bundled with the X-axis fiber optic gyroscope cable and the Z-axis fiber optic gyroscope cable, and then connected to the fiber optic gyroscope connector on the system board; the three accelerometer cables are bundled and connected to the accelerometer connector 63 on the system board; the cables on the power board are bundled and connected to the power connector on the system board; the 15-core connector and the 25-core connector cables are bundled and connected to the external connector on the system board. Arrange all the cables and fix them to the cable fixing holes of the main frame with wire clips.

[0128] Step 6: Install the system board. The specific steps are as follows:

[0129] The system board 6 is fixed to the system board mounting boss 19 with screws.

[0130] Step 7: Install the side panels. The specific method is as follows:

[0131] The two side panels 2 are fixed to the two open end surfaces of the main frame 1 with screws.

[0132] Working principle: The three fiber optic gyroscopes and the three accelerometers send the carrier angular velocity information and acceleration information to the system board 6. After preliminary processing of the data, the system board 6 sends it to the external computer through the external connector. After settlement by the external computer, the navigation information such as carrier velocity, angular velocity, position, and attitude can be obtained.

[0133] In summary, the fiber optic inertial navigation system of the invention includes a main frame, an accelerometer bracket, a fiber optic gyroscope, an accelerometer, a system board, and a power board. The structure of the present invention is compact, the space utilization rate is high, the weight is light, the volume is small, and it has good heat dissipation and earthquake resistance. The mounting hole of the present invention is arranged on the inner side of the main frame, making full use of the space above the mounting hole. The present invention uses a precise main frame weight reduction design so that the center of mass of the entire system is located directly below the centroid, which can greatly improve the earthquake resistance of the system. The present invention disperses the heat generated by the system power supply to the entire main frame, and then directly dissipates the heat to the external environment through the side wall of the main frame, which greatly improves the heat dissipation capacity of the system. The present invention makes the system compact, and based on the use of a 98mm diameter fiber optic gyroscope, its overall size is only 110mm×154mm×154mm.

[0134] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A fiber optic inertial navigation system, characterized in that: include: A main frame (1) having three fiber optic gyroscope mounting surfaces arranged orthogonally to each other; An accelerometer bracket (5) fixed inside the main frame (1); Three fiber optic gyroscopes, which are mounted on the fiber optic gyroscope mounting surface; three accelerometers, the three accelerometers being arranged orthogonally to each other, and the accelerometers are all arranged on the accelerometer bracket (5); A system board (6) mounted on a system board mounting boss (19) provided in the main frame (1); A power board (7) is installed on a power board installation surface (17) provided inside the main frame (1).

2. The fiber optic inertial navigation system according to claim 1, characterized in that: The three fiber optic gyroscopes are respectively an X-axis fiber optic gyroscope (31), a Y-axis fiber optic gyroscope (32), and a Z-axis fiber optic gyroscope (33); the X-axis fiber optic gyroscope (31), the Y-axis fiber optic gyroscope (32), and the Z-axis fiber optic gyroscope (33) are separated from each other by a baffle; the X-axis fiber optic gyroscope (31) and the Y-axis fiber optic gyroscope (32) are arranged on the upper side of the main frame (1), and the Z-axis fiber optic gyroscope (33) is arranged at the bottom of the main frame (1); the accelerometer bracket (5) and the Y-axis fiber optic gyroscope (32) are arranged on the same side of the main frame (1), and the accelerometer bracket (5) and the Y-axis fiber optic gyroscope (32) are separated from each other by a baffle.

3. The fiber optic inertial navigation system according to claim 2, characterized in that: The system board mounting bosses (19) are arranged at the top and bottom of the main frame (1) on which the accelerometer bracket (5) is mounted.

4. The fiber optic inertial navigation system according to claim 3, characterized in that: The power board mounting surface (17) is arranged on the inner side of the main frame (1) on which the accelerometer bracket (5) is mounted, and is located on the inner side of the system board mounting boss (19).

5. The fiber optic inertial navigation system according to claim 1, characterized in that: The accelerometer bracket (5) is provided with an X-axis accelerometer (41), a Y-axis accelerometer (42), and a Z-axis accelerometer (43) which are arranged orthogonally to each other.

6. The fiber optic inertial navigation system according to claim 1, characterized in that: Also includes: Side panels (2) are arranged on both sides of the main frame (1) and are used to cover the outer sides of the fiber optic gyroscope, the accelerometer, the system board (6), and the power board (7); A weight-reducing groove (11) is arranged on the outer side of the main frame (1).

7. The fiber-optic inertial navigation system according to claim 1, characterized in that: Also includes: An external 15-core connector installation groove (12) is embedded in the front face of the main frame (1) so that the connector is located on the inner side of the end face of the main frame (1); The external 25-core connector installation groove (13) is embedded in the front face of the main frame (1) so that the connector is located on the inner side of the end face of the main frame (1).

8. The fiber optic inertial navigation system according to claim 1, characterized in that: The four corners of the bottom of the main frame (1) are each provided with a mounting hole (1C), the mounting hole (1C) does not exceed the four sides of the main frame (1), and the mounting hole (1C) is used to fix an inertial navigation system.

9. The fiber optic inertial navigation system according to claim 1, characterized in that: Also includes: A reinforcing rib (1E) disposed at the bottom of the main frame (1); A first wiring groove (1A) of the main frame, which is arranged inside the main frame (1); The second wiring groove (1B) of the main frame is arranged inside the main frame (1).

10. The fiber optic inertial navigation system according to claim 1, characterized in that: Also includes: Threaded blind holes are arranged at multiple installation surfaces of the main frame (1) and are used to fix cables.

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