Fiber optic integrated navigation device

Abstract

This utility model belongs to the field of unmanned aerial vehicle (UAV) technology and relates to a fiber optic integrated navigation device. The device includes a housing, within which an inertial measurement unit (IMU) is housed. The IMU comprises a three-axis embedded fiber optic gyroscope assembly, which is detachably connected to the housing. A three-axis accelerometer is connected to the bottom of the three-axis embedded fiber optic gyroscope assembly. This utility model adopts a three-axis integrated structure, highly integrating the fiber optic gyroscope assembly, accelerometer, satellite navigation module, and processing circuitry into a compact housing. The components are modularly assembled through detachable connections, significantly reducing size and weight, and adapting to installation requirements in space-constrained scenarios such as aircraft center of gravity. Through miniaturization, high integration, multi-source fusion, and environmental adaptability, this device overcomes the limitations of traditional fiber optic inertial navigation, providing high-precision, high-reliability, and low-cost fiber optic inertial navigation for aviation, maritime, and other fields.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology and relates to a fiber optic integrated navigation device. Background Technology

[0002] Fiber optic integrated navigation equipment is an autonomous navigation and positioning system that fixes inertial devices to a carrier and continuously provides information such as attitude, heading, velocity, and position. It consists of mutually orthogonal three-axis fiber optic gyroscopes, three-axis accelerometer inertial devices, and circuitry.

[0003] With the development of fiber optic inertial technology, the advantages of fiber optic inertial navigation have been further developed. Currently, fiber optic inertial navigation systems are being mass-produced and deployed in the sea, land, air, and civilian fields. However, existing fiber optic inertial navigation systems are large in size and cannot meet the needs of higher precision, lower power consumption, and greater integration. Therefore, there is an urgent need to research a miniaturized fiber optic navigation device to solve the problems of the existing technology. Utility Model Content

[0004] The technical problem to be solved by this utility model is that with the development of fiber optic inertial technology, the advantages of fiber optic inertial navigation have been further developed. At present, fiber optic inertial navigation systems are being mass-produced and equipped in the fields of sea, land, air and civilian use. However, the existing fiber optic inertial navigation systems are large in size and cannot meet the needs of higher precision, lower power consumption and more integration of equipment.

[0005] This utility model discloses a fiber optic integrated navigation device, comprising a housing, within which an inertial measurement unit (IMU) is housed. The IMU includes a three-axis embedded fiber optic gyroscope assembly, detachably connected to the housing. A three-axis accelerometer is connected to the bottom of the IMU, and the bottom of the accelerometer is detachably connected to the housing. A power board and navigation information processing board are detachably mounted on the top of the IMU. A side cover is provided on one side of the housing, on which a satellite navigation component is mounted. Two radio frequency (RF) connectors and one rectangular connector are located on the housing, positioned on opposite sides of the side cover. Based on a miniaturized, three-axis integrated fiber optic strapdown inertial navigation system, the IMU is used to measure the inertial motion parameters of the carrier and perform navigation calculations.

[0006] The satellite navigation component includes a BeiDou dual-antenna module, hexagonal copper pillars, fastening screws, an adapter circuit board, and an adapter board connector. The BeiDou dual-antenna module, adapter circuit board, and adapter board connector are detachably connected to the side cover plate via hexagonal copper pillars and fastening screws.

[0007] The top of the housing is equipped with a top cover plate; the Beidou dual antenna module is used to measure the heading angle of the carrier in real time.

[0008] The three-axis embedded fiber optic gyroscope assembly is used to measure the three-axis angular velocity of the carrier in real time, and the three-axis accelerometer is used to measure the acceleration of the carrier in real time.

[0009] The power board and navigation information processing board are used to perform attitude calculation and navigation algorithm calculation on the measurement data, and the radio frequency connector is used to transmit electromagnetic wave signals to the Beidou dual antenna module.

[0010] The outputs of the inertial measurement unit and the satellite navigation component are connected to the power supply board and navigation information processing board. The housing and top cover are used to prevent the external environment from affecting the inertial measurement unit and to ensure that the inertial measurement unit works normally.

[0011] Compared with the prior art, the beneficial effects of this utility model are as follows: The device adopts a three-axis integrated structure, which highly integrates the fiber optic gyroscope component, accelerometer, satellite navigation module and processing circuit into a compact housing. Each component is modularly assembled through detachable connection, which greatly reduces the size and weight and adapts to the installation requirements of space-constrained scenarios such as the center of gravity of aircraft. Through miniaturization, high integration, multi-source fusion and environmental adaptability design, the device solves the limitations of traditional fiber optic inertial navigation and provides high-precision, high-reliability and low-cost fiber optic inertial navigation for aviation, navigation and other fields.

[0012] By integrating the BeiDou dual-antenna module and the inertial measurement unit, and fusing inertial navigation and satellite navigation data through a tightly coupled Kalman filter algorithm, high-precision attitude and position calculation is achieved, significantly improving positioning accuracy in dynamic environments. The three-axis fiber optic gyroscope and accelerometer measure the angular velocity and acceleration of the carrier in real time, and the ARM processor runs the navigation algorithm in real time to meet the real-time requirements of high-speed moving vehicles. The high-frequency update rate of the BeiDou module further ensures the stability of dynamic positioning. Attached Figure Description

[0013] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0014] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0015] In the diagram: 1. Housing; 2. Three-axis embedded fiber optic gyroscope assembly; 3. Three-axis accelerometer; 4. Top cover plate; 5. Power board & navigation information processing board; 6. Rectangular connector; 7. Side cover plate; 8. Beidou dual antenna module; 9. Hexagonal copper pillar; 10. Fastening screw; 11. Adapter circuit board; 12. Adapter board connector; 13. RF connector. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0017] To enable those skilled in the art to better understand the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.

[0018] It should be noted that, unless otherwise specified, the embodiments and features and technical solutions in the present invention can be combined with each other.

[0019] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0020] Example 1

[0021] like Figure 1As shown, a fiber optic integrated navigation device includes a housing 1, within which an inertial measurement unit (IMU) is housed. The IMU includes a three-axis embedded fiber optic gyroscope assembly 2, detachably connected to the housing 1. A three-axis accelerometer 3 is connected to the bottom of the three-axis embedded fiber optic gyroscope assembly 2, and the bottom of the three-axis accelerometer 3 is detachably connected to the housing 1. A power board and navigation information processing board 5 are detachably mounted on the top of the three-axis embedded fiber optic gyroscope assembly 2. A side cover 7 is provided on one side of the housing 1, on which a satellite navigation component is mounted. Two radio frequency connectors 13 and one rectangular connector 6 are provided on the housing 1, positioned on opposite sides of the side cover 7. Based on a miniaturized three-axis integrated fiber optic strapdown inertial navigation system, the IMU is used to measure the inertial motion parameters of the carrier and perform navigation calculations. The satellite navigation component... The system includes a Beidou dual-antenna module 8, hexagonal copper pillars 9, fastening screws 10, an adapter circuit board 11, and an adapter board connector 12. The Beidou dual-antenna module 8, the adapter circuit board 11, and the adapter board connector 12 are detachably connected to the side cover plate 7 via the hexagonal copper pillars 9 and fastening screws 10. A top cover plate 4 is installed on the top of the housing 1. The Beidou dual-antenna module 8 is used to measure the heading angle of the carrier in real time. The three-axis embedded fiber optic gyroscope assembly is used to measure the three-axis angular velocity of the carrier in real time. The three-axis accelerometer 3 is used to measure the acceleration of the carrier in real time. The power board & navigation information processing board 5 is used to perform attitude calculation and navigation algorithm calculation on the measurement data. The RF connector 13 is used to transmit electromagnetic wave signals to the Beidou dual-antenna module 8. The outputs of the inertial measurement unit and the satellite navigation assembly are connected to the power board & navigation information processing board 5. The housing 1 and the top cover plate 4 are used to prevent the external environment from affecting the inertial measurement unit and to ensure the normal operation of the inertial measurement unit.

[0022] The three-axis embedded fiber optic gyroscope assembly 2 includes a main support, a gyroscope control box, and orthogonally mounted X / Y / Z-axis fiber optic gyroscopes; a power board & navigation information processing board 5 executes a multi-source fusion navigation algorithm, including tightly coupled Kalman filtering to fuse inertial navigation and satellite navigation data; and a Beidou dual-antenna module 8 is equipped with a carrier phase differential positioning module with a positioning update rate ≥10Hz.

[0023] During operation: The housing 1 and the entire device are fixed to the center of gravity of the aircraft by external bolts. The radio frequency connector 13 is connected to the satellite navigation antenna. During initial alignment, the Beidou dual antenna on the Beidou dual antenna module 8 measures the true north direction, the three-axis embedded fiber optic gyroscope and the entire inertial measurement unit compensate for the angular motion of the carrier, and then outputs attitude / position data at 200Hz for flight navigation.

[0024] The device uses a three-axis embedded fiber optic gyroscope assembly 2 and a three-axis accelerometer 3 as its core inertial components. The navigation information processing board collects angular velocity and acceleration data from the gyroscope and accelerometer in real time and performs temperature error compensation and dynamic error compensation. The alignment and integrated navigation algorithm is embedded in the ARM processor of the navigation information processing board. It receives initial velocity, position, heading and other information provided by the satellite module in real time, performs integrated navigation calculations, and outputs the carrier's heading angle, roll angle, pitch angle, position (longitude, latitude and elevation) information and velocity information through the RS422 interface. The device adopts a three-axis integrated structure, highly integrating the fiber optic gyroscope assembly, accelerometer, satellite navigation module and processing circuit into a compact housing 1. Through miniaturization, high integration, multi-source fusion and environmental adaptability design, it solves the limitations of traditional fiber optic inertial navigation and provides high-precision, high-reliability and low-cost fiber optic inertial navigation for aviation, navigation and other fields.

[0025] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the present utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the present utility model, thereby enabling those skilled in the art to better understand and utilize it. The present utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A combined optical fiber navigation device comprising a housing (1), characterized in that: An inertial measurement unit is provided inside the housing (1). The inertial measurement unit includes a three-axis embedded fiber optic gyroscope assembly (2). The three-axis embedded fiber optic gyroscope assembly (2) is detachably connected inside the housing (1). A three-axis accelerometer (3) is connected to the bottom of the three-axis embedded fiber optic gyroscope assembly (2), and the bottom of the three-axis accelerometer (3) is detachably connected to the housing (1). A power board and navigation information processing board (5) are detachably installed on the top of the three-axis embedded fiber optic gyroscope assembly (2). A side cover plate (7) is provided on one side of the housing (1). A satellite navigation assembly is provided on the side cover plate (7). Two radio frequency connectors (13) and one rectangular connector (6) are provided on the housing (1). The two radio frequency connectors (13) and one rectangular connector (6) are located on the side of the side cover plate (7) on the housing (1). Based on the miniaturized fiber optic strapdown inertial navigation system with three axes, the inertial measurement unit is used to complete the measurement of the carrier's inertial motion parameters and navigation calculation.

2. The fiber optic integrated navigation device according to claim 1, characterized in that: The satellite navigation component includes a Beidou dual antenna module (8), a hexagonal copper pillar (9), a fastening screw (10), an adapter circuit board (11), and an adapter board connector (12). The Beidou dual antenna module (8), the adapter circuit board (11), and the adapter board connector (12) are detachably connected to the side cover plate (7) via the hexagonal copper pillar (9) and the fastening screw (10).

3. The fiber optic integrated navigation device according to claim 2, characterized in that: The top of the housing (1) is fitted with a top cover plate (4); the Beidou dual antenna module (8) is used to measure the heading angle of the carrier in real time.

4. The fiber optic integrated navigation device according to claim 2, characterized in that: The three-axis embedded fiber optic gyroscope assembly is used to measure the three-axis angular velocity of the carrier in real time, and the three-axis accelerometer (3) is used to measure the acceleration of the carrier in real time.

5. The fiber optic integrated navigation device according to claim 4, characterized in that: The power board and navigation information processing board (5) are used to perform attitude calculation and navigation algorithm calculation on the measurement data, and the radio frequency connector (13) is used to transmit electromagnetic wave signals to the Beidou dual antenna module (8).

6. The fiber optic integrated navigation device according to claim 5, characterized in that: The output of the inertial measurement unit and the satellite navigation component is connected to the power supply board and navigation information processing board (5). The housing (1) and the top cover (4) are used to prevent the external environment from affecting the inertial measurement unit and to ensure that the inertial measurement unit works normally.

Images