CN221147635U - MEMS combined navigation system structure with embedded magnetic heading sensor and satellite receiver - Google Patents
MEMS combined navigation system structure with embedded magnetic heading sensor and satellite receiver Download PDFInfo
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- CN221147635U CN221147635U CN202322900805.9U CN202322900805U CN221147635U CN 221147635 U CN221147635 U CN 221147635U CN 202322900805 U CN202322900805 U CN 202322900805U CN 221147635 U CN221147635 U CN 221147635U
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- heading sensor
- satellite receiver
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- 238000005259 measurement Methods 0.000 claims abstract description 21
- 238000004891 communication Methods 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 3
- 239000003990 capacitor Substances 0.000 abstract 1
- 239000000306 component Substances 0.000 description 17
- 239000008358 core component Substances 0.000 description 7
- 238000013461 design Methods 0.000 description 6
- 230000001133 acceleration Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 230000003044 adaptive effect Effects 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- 238000004132 cross linking Methods 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
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Abstract
The utility model discloses an MEMS combined navigation system structure embedded with a magnetic heading sensor and a satellite receiver, which comprises a shell, an in-shell component and an upper cover plate component, wherein the in-shell component is arranged in an inner cavity of the shell, the upper cover plate component is arranged at the top of the shell, the in-shell component comprises a capacitor, an external socket, an MEMS inertial measurement unit, a motherboard, a power panel and an antenna socket, the upper cover plate component comprises an upper cover plate, a gasket, the magnetic heading sensor and the satellite receiver, the upper cover plate, the gasket and the magnetic heading sensor are connected through antimagnetic screws, the satellite receiver is connected with the upper cover plate through a receiver strut, and a switching circuit board is further connected to the lower part of one side of the satellite receiver. Solves the existing problems.
Description
Technical Field
The utility model relates to the field of navigation system structures, in particular to an MEMS combined navigation system structure with an embedded magnetic heading sensor and a satellite receiver.
Background
The navigation structure can be applied to various scenes, the existing navigation structure is simple in structure and single in function, only one of a local magnetic heading sensor and a satellite receiver is often carried, so that comprehensive navigation cannot be realized, the existing navigation structure also has the problem that design among internal structures is unreasonable, and the installation error of a core component is large, so that the accuracy of an inertial device cannot be guaranteed.
Disclosure of utility model
The utility model aims to provide an MEMS combined navigation system structure with an embedded magnetic heading sensor and a satellite receiver, which solves the existing problems.
In order to solve the technical problems, the utility model adopts the following technical scheme:
The utility model provides an embedded magnetic heading sensor and satellite receiver's MEMS integrated navigation system structure, includes casing, shell internal components and parts and upper cover plate subassembly, and shell internal components sets up in the inner chamber of casing, upper cover plate subassembly sets up at the top of casing, shell internal components includes electric capacity, external socket, MEMS inertial measurement unit, motherboard, power strip and antenna socket, upper cover plate subassembly includes upper cover plate, liner, magnetic heading sensor and satellite receiver, link to each other through antimagnetic screw between upper cover plate, liner, the magnetic heading sensor, satellite receiver passes through the receiver pillar and links to each other with the upper cover plate, the lower part of satellite receiver one side still has the switching circuit board.
The shell adopts solid aluminum, the bottom contact surface is subjected to conductive oxidation treatment, a reasonable layout structure and design are carried out in the shell to meet the requirement of electromagnetic compatibility, and a magnetic heading sensor and a satellite receiver are integrated in the system; the geomagnetic information can be sensitive, the output of the magnetic heading sensor is realized, the interference of the backup heading state on the magnetic heading sensor can be corrected, and the accurate output of the magnetic heading is realized; the BD3 frequency band can be supported, differential positioning is supported, and adaptive recognition of a differential input RTCM format is realized; the motherboard can establish a mathematical platform and navigation attitude calculation and provide a data cross-linking interface; the power panel provides power supply for each inertial device and function circuit; the power supply inlet processing module is mainly used for protecting the power supply characteristics and electromagnetic compatibility of an inlet power supply; the flight direction of the magnetic heading sensor is consistent with the flight direction of the system, and the magnetic heading sensor and the power panel keep a certain heat convection distance to ensure the heat dissipation requirement of the receiver; the satellite receiver is fixed on the upper cover plate through the receiver support column and keeps a distance from the magnetic heading sensor, so that the structure can reduce the installation error of core components and ensure the precision of inertial devices.
As a further preferred mode of the utility model, the shell and the upper cover plate component are of an integrated structure, the grounding mode adopts single-point grounding, the upper cover plate component is provided with a step-shaped contact surface, the upper cover plate component is tightly combined with the shell through the step-shaped contact surface, and conductive rubber sealing gaskets are arranged between the upper cover plate component and the shell and between the components in the shell and the contact surface in the shell.
As a further preferable aspect of the present utility model, the MEMS inertial measurement unit is directly processed with a mounting surface and a reference abutment surface on its outer housing by a high precision machine, and the MEMS inertial measurement unit is fixed to the bottom mounting surface of the housing by mounting screws.
The MEMS inertial measurement unit is a core component of the structure and is used for sensing and measuring the triaxial angular velocity and acceleration, the MEMS inertial measurement unit is fixed on the bottom mounting surface of the shell through a mounting screw, and meanwhile, the mounting error of the MEMS inertial measurement unit is ensured through a reference leaning surface, so that the precision of an inertial device is ensured.
As a further preferable mode of the utility model, an inner cavity is processed in the middle of the bottom surface of the upper cover plate, mounting bosses are processed at four corners of the bottom of the inner cavity, the magnetic heading sensor is fixed with the mounting bosses through antimagnetic screws, and the inner cavity can completely cover the magnetic heading sensor.
The inner cavity can completely cover the magnetic heading sensor, and the influence of external factors can be reduced.
As a further preferred aspect of the present utility model, the motherboard design serial port communication has multiple RS-422 and RS-232 buses.
Compared with the prior art, the utility model can at least achieve one of the following beneficial effects:
1. The shell adopts solid aluminum, the bottom contact surface is subjected to conductive oxidation treatment, a reasonable layout structure and design are carried out in the shell to meet the requirement of electromagnetic compatibility, and a magnetic heading sensor and a satellite receiver are integrated in the system; the geomagnetic information can be sensitive, the output of the magnetic heading sensor is realized, the interference of the backup heading state on the magnetic heading sensor can be corrected, and the accurate output of the magnetic heading is realized; the BD3 frequency band can be supported, differential positioning is supported, and adaptive recognition of a differential input RTCM format is realized; the motherboard can establish a mathematical platform and navigation attitude calculation and provide a data cross-linking interface; the power panel provides power supply for each inertial device and function circuit; the power supply inlet processing module is mainly used for protecting the power supply characteristics and electromagnetic compatibility of an inlet power supply; the flight direction of the magnetic heading sensor is consistent with the flight direction of the system, and the magnetic heading sensor and the power panel keep a certain heat convection distance to ensure the heat dissipation requirement of the receiver; the satellite receiver is fixed on the upper cover plate through the receiver support column and keeps a distance from the magnetic heading sensor, so that the structure can reduce the installation error of core components and ensure the precision of inertial devices.
2. The MEMS inertial measurement unit is a core component of the structure and is used for sensing and measuring the triaxial angular velocity and acceleration, the MEMS inertial measurement unit is fixed on the bottom mounting surface of the shell through a mounting screw, and meanwhile, the mounting error of the MEMS inertial measurement unit is ensured through a reference leaning surface, so that the precision of an inertial device is ensured.
3. The inner cavity can completely cover the magnetic heading sensor, and the influence of external factors can be reduced.
4. The structure can respectively measure the angular rate and the acceleration of a machine body through an MEMS measuring unit directly fixedly connected with the base, and then calculates the heading, the pitching and the inclination angle of the carrier in real time through a mathematical platform; the geomagnetic sensor can also be sensitive to geomagnetic information, so that the output of the magnetic heading sensor is realized, the interference generated by the magnetic heading sensor can be corrected by the MEMS integrated navigation system, and the accurate output of the magnetic heading is realized; the receiver is embedded, can support BD3 frequency band, and supports differential positioning, and differential input RTCM format self-adaptive identification. Under the condition of not resorting to an external heading reference, the initial heading can be obtained through the magnetic heading sensor, and the heading of the product is corrected through the magnetic heading when the product is used for a long time, so that the long-term heading precision is ensured.
5. Has small volume (length x width x height: 80mm x 99mm x 90 mm) and light weight (less than 0.6 kg); reasonable in design (effectively lay out magnetic heading sensor, satellite receiver and MEMS measuring unit), the function is comprehensive (can receive BDS 3 generation, GPS satellite information, support differential positioning, can provide magnetic heading, possess interface bus such as RS422, RS 232), can realize single LRU accurate course, gesture output.
Drawings
Fig. 1 is a schematic structural view of the present utility model.
Fig. 2 is an exploded view of the structure of the present utility model.
FIG. 3 is a schematic structural view of the upper cover plate assembly of the present utility model.
Fig. 4 is a schematic structural view of the upper cover plate of the present utility model.
Fig. 5 is a schematic view of a housing structure according to the present utility model.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, based on the embodiments of the utility model, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the utility model.
In addition, the embodiments of the present utility model and the features of the embodiments may be combined with each other without collision.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present utility model, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, or are directions or positional relationships conventionally understood by those skilled in the art, are merely for convenience of describing the present utility model and for simplifying the description, and are not to indicate or imply that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
Specific example 1:
Fig. 1, fig. 2, fig. 3, fig. 4, fig. 5 show a MEMS integrated navigation system structure of embedded magnetic heading sensor and satellite receiver, including casing 1, in-casing components and parts and upper cover plate subassembly, in-casing components set up in the inner chamber of casing 1, upper cover plate subassembly sets up at the top of casing 1, in-casing components include electric capacity 2, external socket 3, MEMS inertial measurement unit 4, motherboard 5, power strip 6 and antenna socket 7, upper cover plate subassembly includes upper cover plate 8, liner 9, magnetic heading sensor 10 and satellite receiver 11, link to each other through antimagnetic screw 12 between upper cover plate 8, liner 9, the magnetic heading sensor 10, satellite receiver 11 links to each other with upper cover plate 8 through receiver pillar 13, the lower part of satellite receiver 11 one side still has switching circuit board 14.
The shell adopts solid aluminum, the bottom contact surface is subjected to conductive oxidation treatment, a reasonable layout structure and design are carried out in the shell to meet the requirement of electromagnetic compatibility, and a magnetic heading sensor and a satellite receiver are integrated in the system; the geomagnetic information can be sensitive, the output of the magnetic heading sensor is realized, the interference of the backup heading state on the magnetic heading sensor can be corrected, and the accurate output of the magnetic heading is realized; the BD3 frequency band can be supported, differential positioning is supported, and adaptive recognition of a differential input RTCM format is realized; the motherboard can establish a mathematical platform and navigation attitude calculation and provide a data cross-linking interface; the power panel provides power supply for each inertial device and function circuit; the power supply inlet processing module is mainly used for protecting the power supply characteristics and electromagnetic compatibility of an inlet power supply; the flight direction of the magnetic heading sensor is consistent with the flight direction of the system, and the magnetic heading sensor and the power panel keep a certain heat convection distance to ensure the heat dissipation requirement of the receiver; the satellite receiver is fixed on the upper cover plate through the receiver support column and keeps a distance from the magnetic heading sensor, so that the structure can reduce the installation error of core components and ensure the precision of inertial devices.
Specific example 2:
The embodiment is to further explain the casing 1 on the basis of the specific embodiment 1, the casing 1 and the upper cover plate component are of an integrated structure, the grounding mode adopts single-point grounding, the upper cover plate component is provided with a step-shaped contact surface, the upper cover plate component is tightly combined with the casing 1 through the step-shaped contact surface, and conductive rubber sealing gaskets are arranged between the upper cover plate component and the casing 1 and between the in-casing components and the in-casing contact surface.
Specific example 3:
In this embodiment, the MEMS inertial measurement unit 4 is further described on the basis of embodiment 1, where the MEMS inertial measurement unit 4 is directly machined on its housing to form a mounting surface and a reference abutment surface by a high-precision machine, and the MEMS inertial measurement unit 4 is fixed to the bottom mounting surface of the housing by mounting screws.
The MEMS inertial measurement unit is a core component of the structure and is used for sensing and measuring the triaxial angular velocity and acceleration, the MEMS inertial measurement unit is fixed on the bottom mounting surface of the shell through a mounting screw, and meanwhile, the mounting error of the MEMS inertial measurement unit is ensured through a reference leaning surface, so that the precision of an inertial device is ensured.
Specific example 4:
In this embodiment, the upper cover plate 8 is further described on the basis of embodiment 1, an inner cavity is machined in the middle of the bottom surface of the upper cover plate 8, mounting bosses 81 are machined at four corners of the bottom of the inner cavity, the magnetic heading sensor 10 and the mounting bosses 81 are fixed by the anti-magnetic screws 12, and the inner cavity can completely cover the magnetic heading sensor 10.
The inner cavity can completely cover the magnetic heading sensor, and the influence of external factors can be reduced.
Specific example 5:
The present embodiment further describes the motherboard 5 based on embodiment 1, and the motherboard 5 is designed to have multiple RS-422 and RS-232 buses for serial communication.
Although the present utility model has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements and changes may be made without departing from the spirit and principles of the present utility model.
Claims (5)
1. An embedded magnetic heading sensor and satellite receiver's MEMS integrated navigation system structure, its characterized in that: including casing (1), in-shell components and parts and upper cover plate subassembly, in-shell components set up in the inner chamber of casing (1), upper cover plate subassembly sets up the top at casing (1), in-shell components include electric capacity (2), external socket (3), MEMS inertial measurement unit (4), motherboard (5), power strip (6) and antenna socket (7), upper cover plate subassembly includes upper cover plate (8), liner (9), magnetic heading sensor (10) and satellite receiver (11), link to each other through antimagnetic screw (12) between upper cover plate (8), liner (9), magnetic heading sensor (10), satellite receiver (11) link to each other with upper cover plate (8) through receiver pillar (13), the lower part of satellite receiver (11) one side still is connected with switching circuit board (14).
2. The MEMS integrated navigation system architecture of an embedded magnetic heading sensor and satellite receiver of claim 1, wherein: the shell body (1) and the upper cover plate component are of an integrated structure, the grounding mode adopts single-point grounding, the upper cover plate component is provided with a step-shaped contact surface, the upper cover plate component is tightly combined with the shell body (1) through the step-shaped contact surface, and conductive rubber sealing gaskets are arranged between the upper cover plate component and the shell body (1) and between the in-shell components and parts and the in-shell contact surface.
3. The MEMS integrated navigation system architecture of an embedded magnetic heading sensor and satellite receiver of claim 1, wherein: the MEMS inertial measurement unit (4) is directly processed into a mounting surface and a reference leaning surface on the shell of the MEMS inertial measurement unit through a high-precision machine, and the MEMS inertial measurement unit (4) is fixed on the bottom mounting surface of the shell through a mounting screw.
4. The MEMS integrated navigation system architecture of an embedded magnetic heading sensor and satellite receiver of claim 1, wherein: an inner cavity is formed in the middle of the bottom surface of the upper cover plate (8), mounting bosses (81) are formed in four corners of the bottom of the inner cavity, the magnetic heading sensor (10) and the mounting bosses (81) are fixed through antimagnetic screws (12), and the inner cavity can completely cover the magnetic heading sensor (10).
5. The MEMS integrated navigation system architecture of an embedded magnetic heading sensor and satellite receiver of claim 1, wherein: the motherboard (5) is designed with serial communication with multiple paths of RS-422 and RS-232 buses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322900805.9U CN221147635U (en) | 2023-10-27 | 2023-10-27 | MEMS combined navigation system structure with embedded magnetic heading sensor and satellite receiver |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322900805.9U CN221147635U (en) | 2023-10-27 | 2023-10-27 | MEMS combined navigation system structure with embedded magnetic heading sensor and satellite receiver |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221147635U true CN221147635U (en) | 2024-06-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322900805.9U Active CN221147635U (en) | 2023-10-27 | 2023-10-27 | MEMS combined navigation system structure with embedded magnetic heading sensor and satellite receiver |
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| Country | Link |
|---|---|
| CN (1) | CN221147635U (en) |
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2023
- 2023-10-27 CN CN202322900805.9U patent/CN221147635U/en active Active
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