CN202008366U - Miniature inertia navigation system - Google Patents
Miniature inertia navigation system Download PDFInfo
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- CN202008366U CN202008366U CN2010206516995U CN201020651699U CN202008366U CN 202008366 U CN202008366 U CN 202008366U CN 2010206516995 U CN2010206516995 U CN 2010206516995U CN 201020651699 U CN201020651699 U CN 201020651699U CN 202008366 U CN202008366 U CN 202008366U
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- data processing
- navigation system
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- processing plate
- inertial navigation
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Abstract
The utility model relates to a miniature inertia navigation system, which belongs to the technical field of navigation, guidance and control. An external structure of the miniature inertia navigation system consists of an installing base (1) and an outer cover (7), wherein an internal inertia assembly is fixed on the installing base (1) through a shock absorption device (3), an inertia assembly consists of a gyroscope combination (8), an acceleration meter plate (6), a data processing plate (5) and a support frame (2), the gyroscope combination (8), the acceleration meter plate (6) and the data processing plate (5) are respectively fixed on the support frame (2) and are connected through a cable or a connector assembly, and the data processing plate (5) realizes the electric connection with external equipment through a socket (4). The data processing plate (5) is integrated with a high-precision analog-to-digital (A/D) module, a direct current/direct current (DC/DC) power supply module, a central processing unit (CPU) combined module and a serial communication module.
Description
Technical field
The utility model relates to a kind of miniature inertial navigation system, and the utility model can provide three axial velocity informations, positional information and attitude informations in the inertial space for carrier.The utility model belongs to the Navigation, Guidance and Control technical field, can be widely used in the association area of small-sized carrier control such as Aeronautics and Astronautics, geologic prospecting, industrial measurement and control, robot, robot pilot, platform control.
Background technology
Inertial navigation system can provide three axial velocity informations, positional information and attitude informations etc. in the inertial space for carrier.Thereby can constitute the GPS/ inertia combined navigation system and improve position and velocity accuracy and attitude accuracy when inertial navigation system and GPS make up.Inertial navigation system can also constitute integrated navigation system with aspect sensors such as magnetic compass or star sensors in addition.Inertial navigation system is one of control system most important component, wherein is used for the inertial sensor spare of slotted line acceleration and angular velocity: accelerometer and gyroscope are again the most important sensors of inertial navigation system.
MEMS (micro electro mechanical system) (MEMS-Micro Electro-Mechanical Systems) is to grow up on the basis of microelectric technique, it utilizes the little processing of silicon, electroplates multiple micro-processing technologies such as template duplicating (LIGA) and precision optical machinery processing, and uses the intelligent micro device or the system that integrate micro mechanism, microsensor, miniature actuator and signal Processing and control circuit, communication interface and power supply etc. that modern information technologies constitute.Make inertial sensor spare with the MEMS technology, have only the finger nail size, and can make SMD structure and be welded direct on the circuit board, overturned the volume notion of conventional inertia Sensitive Apparatus.The inertial device that utilizes MEMS inertial sensor spare to form, as inertial navigation system, its volume is little, and is in light weight, low in energy consumption, is subjected to increasing attention, becomes a new direction of Navigation, Guidance and Control technical field development.This series products has all obtained in the dual-use field of the U.S. using widely.The MEMS inertia device is compared with traditional laser, fiber-optic inertial device, and precision is relatively low.How to utilize the MEMS inertial sensor spare of low precision, reach the higher inertial measuring unit of precision and just become the great difficult problem that needs overcome.The utility model is selected MEMS inertial sensor spare (mems accelerometer and MEMS gyroscope) for use, utilize structural design, circuit design, error compensation, special modes such as Kalman filtering algorithm, develop a kind of miniature inertial navigation system, satisfied the demand of degree of precision application conditions.
Summary of the invention
The purpose of this utility model provides that a kind of volume is little, in light weight, low-cost, precision is high, be convenient to the inertial navigation system of installing and using.
This miniature inertial navigation system, its external structure is made up of mounting base (1) and outer cover (7), and inner inertia assembly is fixed on the mounting base (1) by shock attenuation device (3); The inertia assembly is made up of gyroscope combination (8), accelerometer plate (6), data processing plate (5) and support (2); Gyroscope combination (8), accelerometer plate (6) and data processing plate (5) are separately fixed on the support (2); Gyroscope combination (8), accelerometer plate (6) are connected with cable or connector with data processing plate (5), and data processing plate (5) is electrically connected by socket (4) realization and external unit.
The utility model adopts the 10V～40V supply voltage of widespread usage, standard RS485 or RS422 serial communication interface.
The utility model collection MEMS sensor technology, high-precision digital data acquisition and storage, processing and structural design are one, velocity information, positional information and the attitude information of motion carrier three axles in inertial space can be provided, inertial navigation system can be carried out crosslinked with GPS in addition, constitute the GPS/ inertia combined navigation system, thereby improve position and velocity accuracy.
External structure of the present utility model is made up of mounting base and outer cover, and inside is fixed on the inertia assembly on the mounting base by shock attenuation device.The inertia assembly is made up of gyroscope combination, accelerometer circuit board, data processing plate and support, gyroscope combination, accelerometer plate and be fixed on the support after data processing plate is connected with cable or connector.Miniature inertial navigation system is electrically connected by standard socket realization and external device.The utility model structural design compactness, volume is little, and is easy to install and use.By demarcating and error compensation has guaranteed the precision of inertia assembly to have reduced the requirement to structural member machining precision and sensor installation accuracy.The design of shock mitigation system has guaranteed the reliably working of system.
The utility model is integrated modules such as high-precision A/D module, DC/DC power module, CPU composite module and serial communication on hardware design, by demarcating and error compensation has improved the precision of inertial navigation system under the equal sensor accuracy greatly.
The utility model is mainly used in speed, position and the attitude control of Navigation, Guidance and Control technical field motion carrier.
Description of drawings
Accompanying drawing is a structural representation of the present utility model.
Embodiment
Miniature inertial navigation system, its external structure is made up of mounting base (1) and outer cover (7), and inner inertia assembly is fixed on the mounting base (1) by shock attenuation device (3).The inertia assembly is made up of gyroscope combination (8), accelerometer plate (6), data processing plate (5) and support (2).Gyroscope combination (8), accelerometer plate (6) and data processing plate (5) are separately fixed on the support (2).Gyroscope combination (8), accelerometer plate (6) are connected with cable or connector with data processing plate (5), and data processing plate (5) is electrically connected by socket (4) realization and external unit.
Outer cover (7) is fastened on the mounting base (1), and inner inertia assembly is fixed on the mounting base (1) by shock attenuation device (3).
On data processing plate (5), be integrated with high-precision A/D module, DC/DC power module, CPU composite module and serial communication module.The A/D module is responsible for gathering the output signal of gyroscope combination (8) and accelerometer plate (6), the DC/DC power module provides needed various operating voltage for the circuit part of whole inertial navigation system, the CPU module is responsible for the processing of data, and serial communication module has then been realized the mutual communication between inertial navigation system and the external unit.
Socket (4) is used for power supply to be supplied with and data transmission, adopts general 10V～40V direct supply to power, and carries out PERCOM peripheral communication by standard RS485 or RS422 serial communication interface.
The physical dimension of this miniature inertial navigation system is not more than Ф 80mm * 250mm, and quality is not more than 500g.
Claims (8)
1. miniature inertial navigation system is characterized in that its external structure is made up of mounting base (1) and outer cover (7), and inner inertia assembly is fixed on the mounting base (1) by shock attenuation device (3); The inertia assembly is made up of gyroscope combination (8), accelerometer plate (6), data processing plate (5) and support (2); Gyroscope combination (8), accelerometer plate (6) and data processing plate (5) are separately fixed on the support (2); Gyroscope combination (8), accelerometer plate (6) are connected with cable or connector with data processing plate (5), and data processing plate (5) is electrically connected by socket (4) realization and external unit.
2. miniature inertial navigation system according to claim 1 is characterized in that physical dimension is not more than Ф 80mm * 250mm, and quality is not more than 500g.
3. miniature inertial navigation system according to claim 1 is characterized in that external structure is made up of mounting base (1) and outer cover (7), and outer cover (7) is fastened on the mounting base (1).
4. miniature inertial navigation system according to claim 1 is characterized in that inner inertia assembly is fixed on the mounting base (1) by shock attenuation device (3).
5. miniature inertial navigation system according to claim 1, it is characterized in that the inertia assembly makes up (8), accelerometer plate (6), data processing plate (5) and support (2) by gyroscope and forms, gyroscope (8), accelerometer plate (6) and data processing plate (5) are separately fixed on the support (2).
6. miniature inertial navigation system according to claim 1, it is characterized in that gyroscope combination (8), accelerometer plate (6) are connected with cable or connector with data processing plate (5), data processing plate (5) is electrically connected by socket (4) realization and external unit.
7. miniature inertial navigation system according to claim 1 is characterized in that socket (4) is used for power supply and supplies with and data transmission.
8. miniature inertial navigation system according to claim 1 is characterized in that data processing plate (5) is integrated with high-precision A/D module, DC/DC power module, CPU composite module and serial communication module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206516995U CN202008366U (en) | 2010-12-10 | 2010-12-10 | Miniature inertia navigation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206516995U CN202008366U (en) | 2010-12-10 | 2010-12-10 | Miniature inertia navigation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202008366U true CN202008366U (en) | 2011-10-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206516995U Expired - Fee Related CN202008366U (en) | 2010-12-10 | 2010-12-10 | Miniature inertia navigation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202008366U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110530351A (en) * | 2019-08-30 | 2019-12-03 | 贵州航天控制技术有限公司 | A kind of miniature used group |
| CN110608733A (en) * | 2019-08-29 | 2019-12-24 | 贵州航天控制技术有限公司 | Built-in vibration reduction structure of micro inertial measurement unit |
| CN114858165A (en) * | 2022-07-06 | 2022-08-05 | 河北美泰电子科技有限公司 | Inertial navigation assembly |
-
2010
- 2010-12-10 CN CN2010206516995U patent/CN202008366U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110608733A (en) * | 2019-08-29 | 2019-12-24 | 贵州航天控制技术有限公司 | Built-in vibration reduction structure of micro inertial measurement unit |
| CN110530351A (en) * | 2019-08-30 | 2019-12-03 | 贵州航天控制技术有限公司 | A kind of miniature used group |
| CN114858165A (en) * | 2022-07-06 | 2022-08-05 | 河北美泰电子科技有限公司 | Inertial navigation assembly |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111012 Termination date: 20131210 |