Optical fiber inertial navigation structure

Abstract

The utility model discloses an optical fiber inertial navigation structure, which belongs to the technical field of navigation equipment and comprises a base, an inertial measurement component, a circuit board, a shell component and a mounting seat, the shell assembly is mounted on the base to form a closed space; the inertial measurement assembly, the circuit board and the mounting seat are all positioned in the closed space; the inertial measurement assembly comprises a gyroscope main control board, an inner frame, three gyroscopes and three accelerometers; the inner frame is mounted on the mounting seat; the inner frame is of a hexahedron structure, and three gyroscopes and three accelerometers are installed on the six faces of the inner frame respectively. The circuit board is installed on the inner wall face of the shell assembly, and the heating part of the circuit board faces the inner wall face of the shell assembly. And the gyroscope main control board is mounted on the lower end surface of the mounting seat. The inertial measurement assembly of the inertial navigation system is reasonable and compact in layout through the inner frame and the mounting seat, the circuit board is mounted on the inner wall surface of the shell assembly, heat generated during working is transferred to the external environment through the shell, and the heat dissipation effect can be improved.

Description

TECHNICAL FIELD

[0001] The utility model belongs to navigation equipment technical field, concretely relates to a kind of optical fiber inertial navigation structure. BACKGROUND

[0002] In recent years, the application field of inertial navigation system is more and more extensive, and the requirement is also higher and higher. First, the layout of inertial device (gyroscope and accelerometer) and circuit board (navigation computer board and power supply board) should be reasonable and compact, to meet the requirements of miniaturization and light weight. Secondly, the navigation accuracy of the system during operation should be high. According to the engineering practical experience, if the heat generated by the internal circuit board of the system is not effectively dissipated, it will lead to the reduction of navigation accuracy. Therefore, the heat dissipation problem of the heat generating part of the circuit board should be considered in the structure design, so as to ensure the navigation accuracy of the system and achieve the requirement of high precision. CONTENT OF THE UTILITY MODEL

[0003] Therefore, the utility model provides a kind of optical fiber inertial navigation structure, and the inertial measurement assembly of inertial navigation system is reasonably and compactly laid out by inner frame and mounting seat. The circuit board is installed on the inner wall surface of shell assembly. The heat generated during operation is transmitted to the external environment through the shell, which can improve the heat dissipation effect.

[0004] The utility model is realized by the following technical solutions:

[0005] A kind of optical fiber inertial navigation structure, comprising: base, inertial measurement assembly, circuit board, shell assembly and mounting seat;

[0006] The shell assembly is installed on the base to form a closed space;

[0007] The inertial measurement assembly, the circuit board and the mounting seat are all located in the closed space;

[0008] The inertial measurement assembly comprises: gyroscope master control board, inner frame, three gyroscopes and three accelerometers;

[0009] The inner frame is installed on the upper end surface of the mounting seat. The inner frame is a hexahedron structure, and each surface is processed with a mounting slot. Three gyroscopes are respectively installed in three mounting slots, and three accelerometers are respectively installed in the other three mounting slots. The three gyroscopes are mutually orthogonal, and the three accelerometers are mutually orthogonal.

[0010] The circuit board is installed on the inner wall surface of the shell assembly. The heat generating part of the circuit board faces the inner wall surface of the shell assembly.

[0011] The gyroscope master control board is installed on the lower end surface of the mounting seat.

[0012] The three gyroscopes are electrically connected with the gyroscope master control board, and the gyroscope master control board is electrically connected with the circuit board.

[0013] The three accelerometers are electrically connected with the circuit board.

[0014] Further, the slot surface of each mounting slot with a gyroscope is higher than the end surface of the corresponding gyroscope.

[0015] The slot surface of each mounting slot with an accelerometer is higher than the end surface of the corresponding accelerometer.

[0016] Further, the upper end surface of the mounting seat is processed with a plurality of mounting columns a.

[0017] The inner frame is mounted on the mounting columns a.

[0018] Further, the lower end surface of the mounting seat is processed with a displacement slot a, and a plurality of mounting bosses b are arranged in the displacement slot a.

[0019] The gyroscope master control board is mounted on the mounting bosses b.

[0020] Further, the eight corners of the inner frame are designed as missing corners.

[0021] Further, the circuit board includes a navigation computer board and a power supply board.

[0022] The gyroscope master control board is electrically connected with the power supply board; the three accelerometers are electrically connected with the power supply board; and the navigation computer board is electrically connected with the power supply board.

[0023] The navigation computer board is mounted on the inner wall surface of the side wall a of the shell assembly; and a heat conduction boss a is arranged on the heat generating part of the navigation computer board, and the heat conduction boss a faces the side wall a.

[0024] The power supply board is mounted on the inner wall surface of the side wall b of the shell assembly; and a heat conduction boss b is arranged on the heat generating part of the power supply board, and the heat conduction boss b faces the side wall b.

[0025] Further, the shell assembly is provided with a connector;

[0026] The connector is electrically connected with the power supply board.

[0027] Further, a heat dissipation pad is arranged between the navigation computer board and the inner wall surface of the side wall a.

[0028] A heat dissipation pad is arranged between the power supply board and the inner wall surface of the side wall b.

[0029] Further, the outer wall surface of the shell assembly is processed with a plurality of heat dissipation slots.

[0030] Beneficial effects:

[0031] (1) The utility model discloses a kind of optical fiber inertial navigation structures, inner frame is hexahedron structure, installation slot is processed on each face, three gyroscopes are respectively mounted in three installation slots, three accelerometers are respectively mounted in other three installation slots, the installation slot can make full use of the volume of inner frame, the size of optical fiber inertial navigation structure can be reduced;Circuit board is installed on the inner wall surface of shell assembly, and the heating part on circuit board is towards the inner wall surface of shell assembly, compared with the structure that the past is installed in optical fiber inertial navigation shell assembly interior by mounting bracket, heat generated when circuit board works can be quickly transferred to shell assembly, and it is transferred to atmosphere by shell assembly, to reduce the heat of circuit board to gyroscope and accelerometer caused interference, to further improve the navigation accuracy of optical fiber inertial navigation;The closed space formed by shell assembly and base can protect inertial measurement assembly and circuit board and other devices from collision with external devices and be interfered.

[0032] (2) The utility model discloses a kind of optical fiber inertial navigation structures, the slot surface of each installation slot equipped with gyroscope is higher than the end surface of its corresponding gyroscope, the slot surface of each installation slot equipped with accelerometer is higher than the end surface of its corresponding accelerometer, therefore, installation slot can ensure that gyroscope and accelerometer can be protected, avoid collision with other components due to gyroscope and accelerometer exposure, damage.

[0033] (3) The utility model discloses a kind of optical fiber inertial navigation structures, inner frame is installed on mounting post a, can avoid that inner frame occupies redundant position.

[0034] (4) The utility model discloses a kind of optical fiber inertial navigation structures, the lower end surface of mounting seat is processed with give way slot a, the space required for gyroscope main control board installation can be saved by the give way slot a, to further reduce the size of optical fiber inertial navigation structure.

[0035] (5) The utility model discloses a kind of optical fiber inertial navigation structures, eight corners of inner frame are all designed with corner defect, can reduce the weight of inner frame, to reduce the overall weight of inertial navigation component, realize the light weight of inertial navigation component.

[0036] (6) The utility model discloses a kind of optical fiber inertial navigation structures, heat generating part on navigation computer board is equipped with heat-conducting boss a, heat-conducting boss a is towards side wall a, heat generating part on power board is equipped with heat-conducting boss b, heat-conducting boss b is towards side wall b, the setting of heat-conducting boss a and heat-conducting boss b can speed up heat transfer speed, to improve heat dissipation effect.

[0037] (7) The utility model discloses a kind of optical fiber inertial navigation structures, heat dissipation pad is equipped between the inner wall surface of navigation computer board and side wall a, heat dissipation pad is equipped between power board and side wall b;The heat generated by navigation computer board and power board can be quickly transferred to shell assembly, to further improve heat dissipation speed.

[0038] (8) The optical fiber inertial navigation structure of the utility model, the outer wall surface of the shell is processed with several heat dissipation grooves, the heat dissipation grooves can improve the heat dissipation effect of the optical fiber inertial navigation, and can also reduce the weight of the shell, which is conducive to realizing the light weight of the optical fiber inertial navigation. BRIEF DESCRIPTION OF DRAWINGS

[0039] Figure 1 It is the external structure schematic diagram of the utility model;

[0040] Figure 2 It is the internal frame schematic diagram of the utility model;

[0041] Figure 3 It is the internal frame schematic diagram of the utility model after installing three gyroscopes;

[0042] Figure 4 It is the internal frame schematic diagram of the utility model after installing three accelerometers;

[0043] Figure 5 It is the mounting seat schematic diagram A (upper end) of the utility model;

[0044] Figure 6 It is the mounting seat schematic diagram B (lower end) of the utility model;

[0045] Figure 7 It is the mounting seat schematic diagram of the utility model after installing the internal frame;

[0046] Figure 8 It is the mounting seat schematic diagram of the utility model after installing the main control board;

[0047] Figure 9 It is the base schematic diagram A (upper end) of the utility model;

[0048] Figure 10 It is the base schematic diagram B (lower end) of the utility model;

[0049] Figure 11 It is the base schematic diagram of the utility model after installing the mounting seat B;

[0050] Figure 12 It is the shell schematic diagram of the utility model;

[0051] Figure 13 It is the shell schematic diagram of the utility model after installing the navigation computer board;

[0052] Figure 14 It is the shell schematic diagram of the utility model after installing the power supply board;

[0053] Figure 15 It is the base schematic diagram of the utility model after installing the shell;

[0054] Figure 16 is a schematic view of the upper cover of the utility model;

[0055] Wherein, 1 - base, 11 - mounting boss a, 2 - inertial measurement assembly, 21 - gyroscope, 22 - accelerometer, 23 - gyroscope main control board, 24 - inner frame, 3 - circuit board, 31 - navigation computer board, 32 - power board, 4 - shell assembly, 41 - shell, 42 - upper cover, 5 - mounting seat, 51 - mounting column a, 52 - give way slot a, 53 - mounting boss b, 6 - connector. DETAILED DESCRIPTION

[0056] The utility model is described in detail below in combination with the drawings and examples.

[0057] The embodiment provides a kind of optical fiber inertial navigation structure, as shown in Figure 1 、 Figure 11 、 Figure 14 And Figure 15 It includes: base 1, inertial measurement assembly 2, circuit board 3, shell assembly 4, mounting seat 5, connector 6 and several heat dissipation pads.

[0058] As shown in Figure 9 And Figure 10 A plurality of mounting bosses a11 are machined on the upper end surface of the base 1.The lower end surface of the base 1 is machined with a plurality of countersunk holes a.

[0059] As shown in Figure 5 、 Figure 6 And Figure 11 The mounting seat 5 is installed on the mounting boss a11 of base 1 by screw.The mounting seat 5 is rectangular plate structure, and mounting seat 5 is respectively provided with mounting column a51 at four corners.The lower end surface of the mounting seat 5 is machined with give way slot a52, and a plurality of mounting bosses b53 are arranged in give way slot a52.

[0060] As shown in Figures 2 to 8 The inertial measurement assembly 2 includes: gyroscope main control board 23, inner frame 24, three gyroscopes 21 and three accelerometers.

[0061] The gyroscope main control board 23 is installed on the mounting boss b53 of mounting seat 5.The give way slot a52 of the lower end surface of mounting seat 5 cooperates with the mounting boss a11 on the base 1 to provide sufficient mounting space for gyroscope main control board 23.

[0062] The inner frame 24 is a hexahedron structure, and each face of the inner frame 24 is provided with a blind hole. Among them, three mutually orthogonal blind holes are used as mounting slots a, and the other three mutually orthogonal blind holes are used as mounting slots b. Three gyroscopes 21 are correspondingly installed in the three mounting slots a to form mutual orthogonality. Three accelerometers 22 are correspondingly installed in the mounting slots b to form mutual orthogonality. In this embodiment, each gyroscope 21 and each accelerometer 22 are located inside the inner frame 24 (that is, the slot surface of each mounting slot a is higher than the end surface of the corresponding gyroscope 21, and the slot surface of each mounting slot b is higher than the end surface of the corresponding accelerometer), which can make full use of the space of the inner frame, thereby saving the installation space required for installing the three gyroscopes 21 and the three accelerometers 22, and avoiding collision between the gyroscopes 21 and the accelerometers 22 and other devices. A plurality of through holes a are formed at the four corners of the inner frame 24. The through holes a correspond to the mounting columns a51 on the mounting seat 5 one by one, and the through holes a of the inner frame 24 are connected with the mounting columns a51 through screws.

[0063] In a specific embodiment, the eight corners of the inner frame 24 are designed as missing corners to reduce the weight of the inner frame 24.

[0064] As shown in Figure 1 , Figure 12 and Figure 16 , the shell assembly 4 includes an outer shell 41 and an upper cover 42.

[0065] As shown in Figure 12 , the outer shell 41 is a hollow rectangular parallelepiped structure surrounded by four faces. One open end of the outer shell 41 is fixedly connected with the base 1, and the other open end of the outer shell 41 is fixedly connected with the upper cover 42. The outer shell 41, the base 1 and the upper cover 42 form a closed space, and the inertial measurement assembly 2 is located in the closed space. In this embodiment, the end surface of each open end of the outer shell 41 is provided with a plurality of threaded holes, and the upper end surface of the upper cover 42 is provided with a plurality of countersunk holes b. The countersunk holes a on the base 1 correspond to the threaded holes on the end surface of one open end of the outer shell 41 one by one, and the countersunk screws pass through the countersunk holes a and are threadedly connected with the threaded holes on the end surface of one open end of the outer shell 41. The countersunk holes b on the upper cover 42 correspond to the threaded holes on the end surface of the other open end of the outer shell 41 one by one, and the countersunk screws pass through the countersunk holes b and are threadedly connected with the threaded holes on the end surface of the other open end of the outer shell 41.

[0066] In a specific embodiment, a plurality of heat dissipation grooves are formed on the outer wall surface of each side wall of the outer shell 41, which can not only improve the heat dissipation effect of the fiber-optic inertial navigation system, but also play a role in weight reduction.

[0067] The circuit board 3 is located in the closed space. As shown in Figure 15As shown, the circuit board 3 includes a navigation computer board 31 and a power supply board 32 .

[0068] like Figure 13 As shown, the navigation computer board 31 is screwed to the inner surface of one side wall of the housing 41 (depicted as side wall a). A heat-conducting boss a is provided on the heat-generating portion of the navigation computer board 31, facing side wall a. Heat generated by the navigation computer board 31 during operation is transferred to the housing 41 via the heat-conducting boss a, and then to the atmosphere through the housing 41. This improves heat dissipation and reduces interference with the inertial measurement devices (i.e., the three gyroscopes 21 and the three accelerometers) caused by the heating of the navigation computer board 31.

[0069] In one embodiment, a gap a is set between the heat-conducting boss a of the navigation computer board 31 and the inner surface of the side wall a, and a heat dissipation pad is placed in this gap a. Heat generated by the navigation computer board 31 during operation is directly transferred to the housing 41 via the heat dissipation pad, and then to the atmosphere through the housing 41. The heat dissipation pad increases the contact area between the navigation computer board 31 and the side wall a, thereby further improving the heat dissipation effect.

[0070] like Figure 14 As shown, the power board 32 is screwed to the inner wall of the other side wall of the housing 41 (depicted as side wall b). A heat-conducting boss b is provided on the heat-generating portion of the power board 32, facing side wall b. Heat generated by the power board 32 during operation is transferred to the housing 41 via the heat-conducting boss b, and then to the atmosphere through the housing 41. This improves heat dissipation and reduces interference with the inertial measurement device caused by heat generated by the navigation computer board 31.

[0071] In a specific embodiment, the gap b between the heat-conducting boss b of the power board 32 and the inner wall surface of the side wall b is set to 1 to 2 mm, and a heat dissipation pad is provided in the gap b. The heat generated by the power board 32 during operation is directly transferred to the outer shell 41 through the heat dissipation pad, and then transferred to the atmosphere through the outer shell 41, thereby further improving the heat dissipation effect.

[0072] The three gyroscopes 21 are electrically connected to the gyroscope main control board 23, which is in turn electrically connected to the power board 32. The three accelerometers 22 are electrically connected to the power board 32. The navigation computer board 31 is electrically connected to the power board 32. The power board 32 is electrically connected to the connector 6 on the housing 41, and the power board 32 is connected to an external power source and external devices via the connector 6 on the housing 41. All electrical connections mentioned in this embodiment are achieved via power lines (for transmitting power) and signal lines (for transmitting signals).

[0073] Working principle:

[0074] The electric energy of the external power supply is transmitted to the navigation computer board 31, the three accelerometers 22 and the gyroscope master board 23 through the power board 32, the gyroscope master board 23 transmits the electric energy to the three gyroscopes 21, thereby achieving power supply.

[0075] The angular velocities measured by the three gyroscopes 21 are transmitted to the navigation computer board 31 through the gyroscope master board 23 and the power board 32 in sequence for processing, and the processed data is output to the outside of the fiber-optic inertial navigation device, such as sensors and other devices or equipment, through the power board 32. The linear accelerations measured by the three accelerometers 22 are transmitted to the navigation computer board 31 through the power board 32 in sequence for processing, and the processed data is output to the outside of the fiber-optic inertial navigation device, such as sensors and other devices or equipment, through the power board 32, thereby achieving navigation.

[0076] To sum up, the above is only a preferred embodiment of the present application, and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A fiber optic inertial navigation structure, characterized in that: The application relates to a navigation device, which comprises a base (1), an inertial measurement assembly (2), a circuit board (3), a shell assembly (4) and a mounting seat (5). The shell assembly (4) is mounted on the base (1) to form a closed space. The inertial measurement assembly (2), the circuit board (3) and the mounting seat (5) are located in the closed space. The inertial measurement assembly (2) comprises a gyroscope master control board (23), an inner frame (24), three gyroscopes (21) and three accelerometers (22). The inner frame (24) is mounted on the upper end surface of the mounting seat (5); the inner frame (24) is a hexahedron structure, each surface of which is provided with an installation groove; three gyroscopes (21) are respectively arranged in three installation grooves, and three accelerometers (22) are respectively arranged in the other three installation grooves; the three gyroscopes (21) are orthogonal to each other, and the three accelerometers (22) are orthogonal to each other. The circuit board (3) is mounted on the inner wall surface of the shell assembly (4); the heating part of the circuit board (3) faces the inner wall surface of the shell assembly (4). The gyroscope master control board (23) is mounted on the lower end surface of the mounting seat (5). The three gyroscopes (21) are electrically connected with the gyroscope master control board (23), and the gyroscope master control board (23) is electrically connected with the circuit board (3). The three accelerometers (22) are electrically connected with the circuit board (3). The groove surface of each installation groove provided with the gyroscope (21) is higher than the end surface of the corresponding gyroscope (21).

2. The fiber optic inertial navigation system of claim 1, wherein, The groove surface of each installation groove provided with the accelerometer (22) is higher than the end surface of the corresponding accelerometer (22). The upper end surface of the mounting seat (5) is provided with a plurality of mounting columns a (51).

3. The fiber optic inertial navigation system of claim 1, wherein the fiber optic gyroscope is a fiber optic ring laser gyroscope. The inner frame (24) is mounted on the mounting columns a (51). The lower end surface of the mounting seat (5) is provided with a displacement groove a (52), and a plurality of mounting bosses b (53) are arranged in the displacement groove a (52).

4. The fiber optic inertial navigation system of claim 3, wherein the fiber optic gyroscope is a fiber optic ring laser gyroscope. The gyroscope master control board (23) is mounted on the mounting bosses b (53). Eight corners of the inner frame (24) are designed to be missing.

5. The fiber optic inertial navigation system of claim 1, wherein, The circuit board (3) comprises a navigation computer board (31) and a power supply board (32).

6. The fiber optic inertial navigation system of claim 1, wherein, The gyroscope master control board (23) is electrically connected with the power supply board (32); the three accelerometers (22) are electrically connected with the power supply board (32); and the navigation computer board (31) is electrically connected with the power supply board (32). The navigation computer board (31) is mounted on the inner wall surface of the side wall a of the shell assembly (4); a heat conduction boss a is arranged on the heating part of the navigation computer board (31), and the heat conduction boss a faces the side wall a. The power supply board (32) is mounted on the inner wall surface of the side wall b of the shell assembly (4); a heat conduction boss b is arranged on the heating part of the power supply board (32), and the heat conduction boss b faces the side wall b. The shell assembly (4) is provided with a connector (6).

7. The fiber optic inertial navigation structure according to claim 6, characterized in that: The connector (6) is electrically connected with the power supply board (32). A heat dissipation pad is arranged between the navigation computer board (31) and the inner wall surface of the side wall a.

8. The fiber optic inertial navigation system of claim 6, wherein, A heat dissipation pad is arranged between the power supply board (32) and the inner wall surface of the side wall b. The outer wall surface of the shell assembly (4) is provided with a plurality of heat dissipation grooves.

9. The fiber optic inertial navigation system of any one of claims 1-8, wherein, ​

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