Fiber optic integrated navigation device

Abstract

The utility model belongs to the technical field of unmanned plane, and relates to a fiber combination navigation equipment, including base, the detachable connection of upper cover is had on base, the triaxial optical fiber gyroscope of installation is had on base, the side detachable installation of big dipper double antenna module is had on base, the accelerometer, power board, radio frequency connector and navigation computer circuit board are provided in base, and navigation computer circuit board is electrically connected with accelerometer, power board, radio frequency connector and big dipper double antenna module. The utility model adopts the detachable structure of base and upper cover, and combines the compact layout of big dipper double antenna module, navigation computer and other core components, significantly reduces the volume, satisfies the carrier demand of unmanned plane, small aircraft and other space sensitive, through miniaturization, high integration, multi-source fusion and environmental adaptability design, solves the limitation of traditional fiber optic inertial navigation, provides high-precision, high-reliability, low-cost fiber optic inertial navigation for aviation, navigation 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] Unmanned aerial vehicles (UAVs) are aviation devices that fly by remote control or autonomous programs. They are characterized by their small size, low cost, high flexibility, and ease of use, and are widely used to perform various tasks such as tracking, positioning, communication, telemetry, and information collection. Fiber optic inertial navigation is one of the devices on UAVs.

[0003] Currently, with the development of fiber optic inertial technology, the advantages of fiber optic inertial navigation have been further developed. 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 a need for a fiber optic integrated navigation device that takes into account size, weight, shock and vibration resistance, and is easy to manufacture and install in a modular manner. 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, and fiber optic inertial navigation systems have been 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] The present invention discloses a fiber optic integrated navigation device, comprising a base, a top cover detachably connected to the base, a three-axis fiber optic gyroscope mounted on the base, a Beidou dual-antenna module detachably mounted on one side of the base, an accelerometer, a power board, an RF connector, and a navigation computer circuit board disposed inside the base, the navigation computer circuit board being electrically connected to the accelerometer, the power board, the RF connector, and the Beidou dual-antenna module, and an RF connector and a circular connector disposed on one side of the top cover.

[0006] The power board is electrically connected to the navigation computer circuit board and supplies power to it. The radio frequency connector is connected to the Beidou dual antenna module and provides it with radio frequency signals.

[0007] The adapter connector electrically connects to the circular connector, power board, navigation computer circuit board, and Beidou dual-antenna module.

[0008] The outer shell connects the base and the top cover to form a closed space, which is used to avoid the influence of the external environment on the three-axis fiber optic gyroscope and ensure the normal operation of the three-axis fiber optic gyroscope.

[0009] The Beidou dual-antenna module is used to measure the heading angle of the carrier in real time, and the three-axis fiber optic gyroscope is used to measure the three-axis angular velocity of the carrier in real time.

[0010] Compared with the prior art, the beneficial effects of this utility model are: the device adopts a detachable base and top cover structure, and combines the compact layout of core components such as Beidou dual antenna module and navigation computer, which significantly reduces the size and meets the needs of space-sensitive carriers such as UAVs and small aircraft. 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, marine and other fields. Attached Figure Description

[0011] 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.

[0012] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0013] In the diagram: 1. Base; 2. Top cover; 3. Three-axis fiber optic gyroscope; 4. Beidou dual-antenna module; 5. Accelerometer; 6. Power board; 7. RF connector; 8. Navigation computer circuit board; 9. Adapter connector; 10. Circular connector. Detailed Implementation

[0014] 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.

[0015] 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.

[0016] 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.

[0017] 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.

[0018] Example 1

[0019] like Figure 1As shown, a fiber optic integrated navigation device includes a base 1, a top cover 2 detachably connected to the base 1, a three-axis fiber optic gyroscope 3 mounted on the base 1, a Beidou dual-antenna module 4 detachably mounted on one side of the base 1, an accelerometer 5, a power board 6, an RF connector 7, and a navigation computer circuit board 8 disposed inside the base 1. The navigation computer circuit board 8 is electrically connected to the accelerometer 5, the power board 6, the RF connector 7, and the Beidou dual-antenna module 4. An RF connector 7 and a circular connector 10 are disposed on one side of the top cover 2. The power board 6 is electrically connected to the navigation computer... The circuit board 8 is electrically connected and the power board 6 supplies it with power. The RF connector 7 connects to the Beidou dual antenna module 4 and provides it with RF signals. The adapter connector 9 electrically connects the circular connector 10, the power board 6, the navigation computer circuit board 8, and the Beidou dual antenna module 4. The outer shell connects the base 1 and the top cover 2 to form a closed space to prevent the external environment from affecting the three-axis fiber optic gyroscope 3 and to ensure that the three-axis fiber optic gyroscope 3 works normally. The Beidou dual antenna module 4 is used to measure the heading angle of the carrier in real time, and the three-axis fiber optic gyroscope 3 is used to measure the three-axis angular velocity of the carrier in real time.

[0020] The circular connector 10 connects the carrier to its flight control system, establishing a reliable electrical, signal, and mechanical connection to enable data transmission and power supply; the three-axis fiber optic gyroscope 3 is an X / Y / Z-axis fiber optic gyroscope.

[0021] The Beidou dual-antenna module 4, accelerometer 5, and three-axis fiber optic gyroscope 3, along with the data obtained from the above measurements, perform attitude and navigation algorithm calculations through the navigation computer circuit board 8, and then provide the calculated data to the carrier. The navigation computer circuit board 8 runs a tightly coupled navigation algorithm: the inertial navigation equation is jointly solved with the Beidou observation values. In case of failure, it automatically switches to pure inertial mode, with a position drift rate of <0.3nm / h.

[0022] During operation, the base 1 is installed at the center of gravity of the aircraft by external bolts, and the RF connector 7 is connected to the satellite navigation antenna. During initialization, the self-test is completed after 90 seconds of power-on. The Beidou dual antenna heading calibration measures true north, the three-axis fiber optic gyroscope 3 is zero-biased, and the attitude angle (pitch / roll ±0.01°, heading ±0.05°) and position (latitude / longitude accuracy 0.8m CEP) are output in real time. The data is transmitted to the navigation computer circuit board 8 to complete temperature error compensation and dynamic error compensation before takeoff.

[0023] The device uses a three-axis fiber optic gyroscope 3 and an accelerometer 5 as its core inertial devices. The navigation computer circuit board 8 collects angular velocity and acceleration data from the gyroscope and accelerometer 5 in real time and performs temperature error compensation and dynamic error compensation. The alignment and integrated navigation algorithm is embedded in the MCU processor of the navigation computer circuit board 8. It receives initial velocity, position, heading and other information provided by the Beidou dual antenna module 4 in real time, performs integrated navigation calculations, and outputs the carrier's heading angle, roll angle, pitch angle, position (longitude, latitude and elevation) and velocity information through the RS422 interface.

[0024] The device adopts a detachable structure of base 1 and top cover 2, and combines the compact layout of core components such as Beidou dual antenna module 4 and navigation computer to significantly reduce the size and meet the needs of space-sensitive carriers such as UAVs and small aircraft. 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, marine 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 base (1), characterized in that: The base (1) is detachably connected to the top cover (2), and a three-axis fiber optic gyroscope (3) is installed on the base (1). A Beidou dual antenna module (4) is detachably installed on one side of the base (1). An accelerometer (5), a power board (6), an RF connector (7), and a navigation computer circuit board (8) are provided inside the base (1). The navigation computer circuit board (8) is electrically connected to the accelerometer (5), the power board (6), the RF connector (7), and the Beidou dual antenna module (4). An RF connector (7) and a circular connector (10) are provided on one side of the top cover (2).

2. A fiber optic combined navigation apparatus as in claim 1, wherein: The power board (6) is electrically connected to the navigation computer circuit board (8) and supplies power to it. The radio frequency connector (7) is connected to the Beidou dual antenna module (4) and provides it with radio frequency signals.

3. The fiber optic integrated navigation device according to claim 2, characterized in that: Adapter connector (9) Electrical connection circular connector (10), power board (6), navigation computer circuit board (8), Beidou dual antenna module (4).

4. The fiber optic integrated navigation device according to claim 3, characterized in that: The outer shell connects the base (1) and the top cover (2) to form a closed space, which is used to avoid the external environment from affecting the three-axis fiber optic gyroscope (3) and ensure that the three-axis fiber optic gyroscope (3) works normally.

5. The fiber optic integrated navigation device according to claim 4, characterized in that: The Beidou dual-antenna module (4) is used to measure the heading angle of the carrier in real time, and the three-axis fiber optic gyroscope (3) is used to measure the three-axis angular velocity of the carrier in real time.

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