Two-cabin fiber-optic gyroscope inertial measurement device with compact structure

Abstract

The utility model provides a two-cabin fiber-optic gyroscope inertial measurement device with a compact structure, which comprises a mounting body and a partition plate arranged in the mounting body, and a first cabin and a second cabin are formed in the mounting body through the partition plate; the measuring module is arranged in the first cabin; the power supply module is arranged in the second cabin and is connected with the measuring module; the processing module is arranged in the second cabin and is connected with the measuring module; the external plug connector is arranged on the mounting body; according to the two-cabin fiber-optic gyroscope inertial measurement device with the compact structure, disclosed by the utility model, components can be mounted in a reasonable structure, and heat is isolated through the structures of the two cabins, so that the influence of heat in the second cabin on the interior of the first cabin is avoided; and the overall precision is prevented from being reduced under the condition that the measurement module is influenced.

Description

Technical Field

[0001] The utility model relates to the technical field of inertial navigation systems, in particular to a two-cabin fiber optic gyroscope inertial measurement device with a compact structure. Background Art

[0002] Fiber optic gyro inertial navigation systems (FIGINS) are one of the most widely used inertial navigation systems. They can autonomously and in real time provide comprehensive navigation information, including a vehicle's speed, position, and attitude. Currently, miniaturization and high precision are the main development directions for FIGINS.

[0003] In the prior art, publication number CN112179341A, entitled "A three-axis integrated photonic crystal fiber gyro inertial measurement device for aerospace use"; announcement number CN110823220B, entitled "A three-axis integrated fiber gyro inertial measurement device"; and announcement number CN110823219B, entitled "A miniature low-cost three-axis integrated fiber gyro inertial measurement device" all disclose three-axis integrated fiber gyro inertial measurement devices, and each adopts a miniaturized approach to form its own structure.

[0004] However, in the prior art, in the miniaturization process of the fiber optic gyro inertial measurement device, in order to reduce the overall size, the electronic components and the inertial measurement components are placed together. During actual use, the electronic components will generate heat. After long-term use, the heat generated by the electronic components will reduce the performance of the inertial measurement components, resulting in a decrease in the accuracy of the fiber optic gyro inertial navigation. Utility Model Content

[0005] The purpose of the utility model is to provide a two-compartment fiber optic gyro inertial measurement device with a compact structure, which can solve the above technical problems;

[0006] The utility model provides a compact two-chamber fiber optic gyro inertial measurement device, comprising:

[0007] A mounting body and a partition disposed within the mounting body, wherein the partition forms a first compartment and a second compartment within the mounting body;

[0008] A measurement module is disposed in the first cabin;

[0009] a power supply module, disposed in the second compartment and connected to the measurement module;

[0010] a processing module, disposed in the second compartment and connected to the measurement module;

[0011] The external connector is arranged on the mounting body.

[0012] As a further technical solution, the mounting body includes:

[0013] The shell, the upper cover and the bottom cover, the upper cover is connected to one end of the shell to seal the first cabin; the bottom cover is connected to the other end of the shell to seal the second cabin.

[0014] As a further technical solution, a plurality of heat dissipation fins are provided on the outer surface of the shell.

[0015] As a further technical solution, a plurality of inner supports are further provided in the first cabin, and the measuring modules are provided on the plurality of inner supports.

[0016] As a further technical solution, the measurement module includes:

[0017] The platform is arranged in the first cabin;

[0018] A gyroscope assembly is arranged on the platform;

[0019] The acceleration measurement group is set on the platform.

[0020] As a further technical solution, a plurality of positioning holes are provided on the platform.

[0021] As a further technical solution, shock absorbing devices are provided on both sides of the plurality of positioning holes.

[0022] As a further technical solution, the gyroscope group includes:

[0023] A first gyroscope is provided on the platform;

[0024] a second gyroscope, disposed on one side of the platform;

[0025] a third gyroscope, disposed on the other side of the platform;

[0026] Three straight lines respectively passing through the axes of the first gyroscope, the second gyroscope, and the third gyroscope are perpendicular to each other.

[0027] As a further technical solution, the acceleration measurement group includes:

[0028] A first accelerometer is provided on one side of the platform;

[0029] The second accelerometer and the third accelerometer are both arranged on the other side of the platform;

[0030] The planes where the axes of the first accelerometer, the second accelerometer and the third accelerometer lie are perpendicular to each other.

[0031] As a further technical solution, a mounting hole is provided on the mounting body, and the external connector is arranged in the mounting hole.

[0032] The technical solution of the present invention divides the installation body into a first compartment and a second compartment through a partition, and places the measuring module in the first compartment; the power supply module and the processing module are placed in the second compartment; in this way, during use, the heat generated by the power supply module and the processing module are all placed in the second compartment, and the heat in the second compartment is dissipated through the installation body, thereby avoiding the influence of the power supply module and the processing module on the measuring module in the first compartment; therefore, the influence on the measuring module is reduced, thereby ensuring the overall accuracy; compared with the existing technology, components can be installed in a reasonable structure, and heat isolation is performed through the structure of the two compartments, thereby avoiding the heat in the second compartment from affecting the first compartment, and avoiding the overall accuracy being reduced when the measuring module is affected. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0034] Figure 1 This is a three-dimensional diagram of a compact two-compartment fiber optic gyro inertial measurement device according to the present invention at one angle;

[0035] Figure 2 This is a three-dimensional diagram from another angle of the compact two-compartment fiber optic gyro inertial measurement device of the present invention;

[0036] Figure 3 A three-dimensional diagram of the housing of the present invention at one angle;

[0037] Figure 4 This is a three-dimensional diagram of the housing of the present invention from another angle;

[0038] Figure 5 This is a schematic structural diagram of the housing in the present invention;

[0039] Figure 6 A three-dimensional diagram of the measuring module of the present invention at one angle;

[0040] Figure 7 This is a three-dimensional diagram of the measuring module in the present invention from another angle;

[0041] Figure 8 This is a schematic structural diagram of the interior of the second compartment in the present invention;

[0042] Description of reference numerals:

[0043] 1-mounting body; 11-housing; 12-upper cover; 13-bottom cover; 14-heat sink; 15-inner support; 2-partition; 3-first compartment; 4-second compartment; 5-measuring module; 51-platform; 521-first gyroscope; 522-second gyroscope; 523-third gyroscope; 531-first accelerometer; 532-second accelerometer; 533-third accelerometer; 54-shock absorption device; 6-power supply module; 7-processing module; 8-external connector; 9-mounting hole. DETAILED DESCRIPTION

[0044] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the embodiments. Obviously, the embodiments described are only a part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0045] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present invention.

[0046] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more features. In the description of the present utility model, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a communication between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to the specific circumstances.

[0047] like Figure 1-8 As shown, the utility model proposes a compact two-chamber fiber optic gyro inertial measurement device, comprising:

[0048] The mounting body 1 and a partition 2 disposed within the mounting body 1 form a first compartment 3 and a second compartment 4 within the mounting body 1 through the partition 2. In the present invention, the mounting body 1 includes a housing 11, an upper cover 12, and a bottom cover 13. The upper cover 12 is connected to one end of the housing 11 to seal the first compartment 3; the bottom cover 13 is connected to the other end of the housing 11 to seal the second compartment 4. The housing 11 is divided into the first compartment 3 and the second compartment 4 by the partition 2, and the first compartment 3 and the second compartment 4 are in an independent state. After the internal components are installed, the first compartment 3 and the second compartment 4 are sealed respectively by the upper cover 12 and the bottom cover 13.

[0049] In addition, the outer surface of the housing 11 is provided with a plurality of heat dissipation fins 14; the heat dissipation inside the housing 11 can be better dissipated by the plurality of heat dissipation fins 14, thereby improving the overall heat dissipation effect; Figure 3 or Figure 4 As shown, a mounting base is further provided at the bottom of the housing 11, through which the housing 11 can be connected to the outside, and assembly holes are provided at the four corners of the mounting base, through which the mounting base can be connected to the outside;

[0050] The measurement module 5 is arranged in the first compartment 3; the measurement module 5 is installed and protected by the first compartment 3, as shown in FIG. Figure 3 or Figure 5 As shown, a plurality of inner supports 15 are further provided in the first compartment 3, and the measuring module 5 is provided on the plurality of inner supports 15; in the present invention, preferably, screws are passed through the ends of the measuring module 5 and connected to the plurality of inner supports 15 to achieve fixation of the measuring module 5; preferably, four inner supports 15 are provided, which are respectively connected to the four corners of the measuring module 5 by screws;

[0051] like Figure 6 and Figure 7As shown, the measuring module 5 includes a platform 51, a gyroscope group and an acceleration measuring group. The platform 51 is arranged in the first cabin 3; the gyroscope group is arranged on the platform 51; the acceleration measuring group is arranged on the platform 51; when the measuring module 5 is placed in the first cabin 3, it is connected to a plurality of inner supports 15 through the platform 51. Specifically, a plurality of positioning holes (not shown in the figure) are provided on the platform 51, which can be connected to the inner supports 15 after passing through the positioning holes by bolts; in the present utility model, there are 4 inner supports 15, so the number of positioning holes is also 4; of course, in order to avoid measurement errors, the measuring module 5 is placed in the first cabin 3. The measuring module 5 may be damaged due to vibration during use. Therefore, in the present invention, preferably, shock-absorbing devices 54 are provided on both sides of the plurality of positioning holes. In this way, when fixing with screws, the screws sequentially pass through the shock-absorbing device 54 on one side of the positioning hole, the positioning hole, and the shock-absorbing device 54 on the other side of the positioning hole, and then are fixed to the inner support 15. In this way, the vibration transmitted to the measuring module 5 by the housing 11 can be buffered during subsequent use, thereby improving the service life of the measuring module 5. In the present invention, the preferred shock-absorbing device 54 is a rubber pad.

[0052] like Figure 6 and 7 As shown, the gyroscope group includes a first gyroscope 521, a second gyroscope 522, and a third gyroscope 523. The first gyroscope 521 is arranged on the platform 51; the second gyroscope 522 is arranged on one side of the platform 51; and the third gyroscope 523 is arranged on the other side of the platform 51. Three straight lines passing through the axes of the first gyroscope 521, the second gyroscope 522, and the third gyroscope 523 are perpendicular to each other. In the present invention, the first gyroscope 521 is an X-axis gyroscope, the second gyroscope 522 is a Y-axis gyroscope, and the third gyroscope 523 is a Z-axis gyroscope, which perform measurements in the X, Y, and Z directions respectively.

[0053] The acceleration measurement group includes a first accelerometer 531, a second accelerometer 532 and a third accelerometer 533. The first accelerometer 531 is arranged on one side of the platform 51; the second accelerometer 532 and the third accelerometer 533 are both arranged on the other side of the platform 51; the planes where the axes of the first accelerometer 531, the second accelerometer 532 and the third accelerometer 533 are located are perpendicular to each other; specifically, the first accelerometer 531 measures the X direction, the second accelerometer 532 measures the Y direction, and the third accelerometer 533 measures the Z direction, and the first accelerometer 531, the second accelerometer 532 and the third accelerometer 533 correspond to the first gyroscope 521, the second gyroscope 522 and the third gyroscope 523, respectively.

[0054] Through the structure of the platform 51, the first gyroscope 521, the second gyroscope 522, and the third gyroscope 523 are respectively placed on the platform 51, and the first accelerometer 531, the second accelerometer 532, and the third accelerometer 533 are respectively placed on the platform 51 and arranged corresponding to the first gyroscope 521, the second gyroscope 522, and the third gyroscope 523. By placing all components on the platform 51, the size of the measurement module 5 is further reduced, making the entire unit more compact.

[0055] like Figure 8 As shown, the power supply module 6 is arranged in the second compartment 4 and connected to the measuring module 5; the processing module 7 is arranged in the second compartment 4 and connected to the measuring module 5; the power supply module 6 provides the measuring module 5 with the required power for operation, and the processing module 7 obtains and processes the information of the measuring module 5; in the present utility model, the power supply module 6 and the processing module 7 are both selected from the existing technology, which will not be further described;

[0056] External connector 8 is provided on mounting body 1, and communication with the outside world is achieved through external connector 8. Furthermore, in the present invention, external connector 8 can be connected to processing module 7, or can be simultaneously connected to processing module 7 and measurement module 5, enabling communication between processing module 7 or measurement module 5 and the outside world through external connector 8. Specifically, mounting body 1 is provided with a mounting hole 9, and external connector 8 is disposed within mounting hole 9.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A compact two-chamber fiber optic gyro inertial measurement device, characterized in that: include: A mounting body (1) and a partition (2) disposed within the mounting body (1), wherein a first chamber (3) and a second chamber (4) are formed within the mounting body (1) through the partition (2); a measuring module (5), arranged in the first chamber (3); a power supply module (6), disposed in the second compartment (4) and connected to the measuring module (5); a processing module (7), disposed in the second chamber (4) and connected to the measuring module (5); The external connector (8) is arranged on the mounting body (1).

2. The compact two-chamber fiber optic gyro inertial measurement device according to claim 1, characterized in that: The mounting body (1) comprises: A shell (11), an upper cover (12) and a bottom cover (13), wherein the upper cover (12) is connected to one end of the shell (11) to seal the first chamber (3); and the bottom cover (13) is connected to the other end of the shell (11) to seal the second chamber (4).

3. The compact two-chamber fiber optic gyro inertial measurement device according to claim 2, characterized in that: The outer surface of the housing (11) is provided with a plurality of heat dissipation fins (14).

4. The compact two-chamber fiber optic gyro inertial measurement device according to claim 1, characterized in that: A plurality of inner supports (15) are also provided in the first chamber (3), and the measuring module (5) is provided on the plurality of inner supports (15).

5. The compact two-chamber fiber optic gyro inertial measurement device according to claim 1, characterized in that: The measuring module (5) comprises: A platform (51) is arranged in the first cabin (3); A gyroscope assembly is arranged on the platform (51); An acceleration measurement group is arranged on the platform (51).

6. The compact two-chamber fiber optic gyro inertial measurement device according to claim 5, characterized in that: The platform (51) is provided with a plurality of positioning holes.

7. The compact two-chamber fiber optic gyro inertial measurement device according to claim 6, characterized in that: Shock-absorbing devices (54) are provided on both sides of the plurality of positioning holes.

8. The compact two-chamber fiber optic gyro inertial measurement device according to claim 5, characterized in that: The gyroscope group includes: a first gyroscope (521), disposed on the platform (51); A second gyroscope (522) is arranged on one side of the platform (51); a third gyroscope (523), arranged on the other side of the platform (51); Three straight lines respectively passing through the axes of the first gyroscope (521), the second gyroscope (522) and the third gyroscope (523) are perpendicular to each other.

9. The compact two-chamber fiber optic gyro inertial measurement device according to claim 5, characterized in that: The acceleration measurement group includes: A first accelerometer (531) is arranged on one side of the platform (51); A second accelerometer (532) and a third accelerometer (533) are both arranged on the other side of the platform (51); The planes on which the axes of the first accelerometer (531), the second accelerometer (532) and the third accelerometer (533) lie are perpendicular to each other.

10. The compact two-chamber fiber optic gyro inertial measurement device according to claim 1, characterized in that: The mounting body (1) is provided with a mounting hole (9), and the external connector (8) is arranged in the mounting hole (9).

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