Portable optical space-time standard measurement system

Abstract

The invention discloses a portable optical space-time standard measurement system, and relates to the technical field of integrated navigation, the portable optical space-time standard measurement system comprises a bottom plate, a first frame, a second frame and a third frame, the first frame is sleeved in the second frame, and the second frame is sleeved in the third frame; a three-axis digital accelerometer is mounted in the first frame; a three-axis optical fiber gyroscope is mounted on the second frame; an intelligent navigation computer module and a power conversion module are mounted on the third frame; a top plate is arranged above the second frame, and a power supply module and a binocular vision module are installed on the top plate. Through the arrangement of the invention, the unique module arrangement is adopted to form a multi-layer mutual-embracing type cube space structure in which the modules are distributed in a crossed and staggered manner, so that the limited space can be fully utilized, and the overall volume of the system is greatly reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of combined navigation, in particular to a portable optical time-space standard measurement system. Background Art

[0002] High-resolution airborne remote sensing payload imaging requires the carrier aircraft to perform uniform, smooth, and ideally linear motion. However, due to external airflow disturbances and internal engine vibration, it is difficult for the aircraft to meet these ideal motion requirements. Motion errors can severely degrade the imaging quality of the payload's motion, or even render it impossible to image. Therefore, a spatiotemporal measurement system must be used to accurately measure these motion errors for motion compensation, thereby improving the resolution of the payload imaging. The higher the resolution of airborne ground imaging, the higher the accuracy required for motion error measurement. High-precision spatiotemporal measurement systems primarily consist of a high-precision inertial measurement unit, a global positioning system receiver, an information processing system, and post-processing software. These systems provide high-precision position, velocity, attitude, and time references for various types of unmanned aerial vehicles (UAVs) and manned aircraft ground observation payloads. They have become essential equipment for airborne ground observation systems in completing military reconnaissance and mapping missions, and are a key component in achieving high-resolution, real-time imaging.

[0003] The large size, high cost, and high power consumption of traditional space-time measurement systems have hindered the continued development of airborne Earth observation systems. Currently, to minimize the size and weight of high-precision position and attitude measurement systems, researchers often focus on a single component within the system without considering the integration of power supply and vision modules. This results in low space-time measurement accuracy in complex environments, primarily due to poor anti-interference capabilities and susceptibility to environmental influences.

[0004] Based on this, there is an urgent need for a high-efficiency, high-precision space-time measurement system to meet the application requirements of small and light aviation high platforms. Summary of the Invention

[0005] The purpose of the present invention is to solve the defects in the prior art and to propose a portable optical space-time standard measurement system.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A portable optical space-time standard measurement system includes a base plate, a first frame, a second frame and a third frame, wherein the first frame is nested in the second frame, and the second frame is nested in the third frame; a three-axis digital accelerometer is installed in the first frame; a three-axis fiber optic gyroscope is installed on the second frame; an intelligent navigation computer module and a power conversion module are installed on the third frame; a top plate is provided above the second frame, and a power supply module and a binocular vision module are installed on the top plate.

[0008] Furthermore, the first frame includes two groups of first vertical plates, which are vertically arranged and perpendicular to each other. The three parts of the three-axis digital accelerometer are respectively arranged on the two first vertical plates and the upper end surface of the bottom plate.

[0009] Furthermore, the second frame includes two sets of second vertical plates, which are vertically arranged and perpendicular to each other. The three parts of the three-axis fiber optic gyroscope are respectively arranged on the two second vertical plates and the upper end surface of the first frame.

[0010] Furthermore, the third frame includes two groups of third vertical plates, which are vertically arranged and perpendicular to each other, and the intelligent navigation computer module and the power conversion module are respectively arranged on the two groups of third vertical plates.

[0011] Furthermore, one side of the top plate is provided with an extension plate, and the binocular vision module is fixedly connected to the extension plate and is located on one side of the power supply module.

[0012] Furthermore, the power supply module is electrically connected to a power conversion module, and the power conversion module is used to supply power to the three-axis fiber optic gyroscope, the intelligent navigation computer module and the three-axis digital accelerometer.

[0013] Furthermore, the intelligent navigation computer module is respectively connected to the binocular vision module, the three-axis fiber optic gyroscope and the three-axis digital accelerometer, and is used to receive and process the output data of the three-axis fiber optic gyroscope, the three-axis digital accelerometer, the binocular vision module and the dual GNSS module, and output speed, position, attitude and time information through initial alignment and combined navigation solution.

[0014] Furthermore, the intelligent navigation computer module adopts a ceramic circuit board with a ZYNQ embedded processor as the core; a dual GNSS module is embedded in the intelligent navigation computer module; and the dual GNSS module has two antenna interfaces.

[0015] Beneficial effects

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] Through the arrangement of the present invention, a unique module arrangement is adopted to form a multi-layer mutually embracing cubic space structure in which the modules are staggered and distributed, which can fully utilize the limited space and greatly reduce the overall volume of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0019] Figure 1Schematic diagram of the overall structure of the portable optical space-time standard measurement system.

[0020] Figure 2 This is a schematic diagram of the installation structure of the binocular vision module.

[0021] Figure 3 Schematic diagram of the installation structure of the three-axis fiber optic gyroscope.

[0022] Figure 4 Schematic diagram of the installation structure of the three-axis digital accelerometer.

[0023] In the figure: 1. Intelligent navigation computer module; 2. Power conversion module; 3. Three-axis digital accelerometer; 4. Power supply module; 5. Binocular vision module; 6. Three-axis fiber optic gyroscope. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0025] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention.

[0026] Reference Figure 1-Figure 4 A portable optical space-time standard measurement system includes a base plate, a first frame, a second frame and a third frame. The first frame is arranged in the second frame, and the second frame is arranged in the third frame. A three-axis digital accelerometer 3 is installed in the first frame; a three-axis fiber optic gyroscope 6 is installed on the second frame; an intelligent navigation computer module 1 and a power conversion module 2 are installed on the third frame; a top plate is arranged above the second frame, and a power supply module 4 and a binocular vision module 5 are installed on the top plate.

[0027] The unique module arrangement forms a multi-layer, mutually embraced cube space structure in which the modules are staggered and distributed, which can make full use of the limited space and greatly reduce the overall volume of the system. Among them, the power supply module 4 can be charged externally, so that it does not need an external power supply during operation. The three-axis fiber optic gyroscope and the three-axis digital accelerometer have three sensitive axes for measuring and outputting the angular velocity and ratio of the three axes. The binocular vision module 5 is used to calculate the relative position and posture through the camera.

[0028] In other preferred embodiments, the first frame includes two groups of first vertical plates, which are vertically arranged and perpendicular to each other, and the three parts of the three-axis digital accelerometer 3 are respectively arranged on the two first vertical plates and the upper end surface of the bottom plate.

[0029] Specifically, the second frame includes two sets of second vertical plates, which are vertically arranged and perpendicular to each other. The three parts of the three-axis fiber optic gyroscope 6 are respectively arranged on the two second vertical plates and the upper end surface of the first frame.

[0030] The third frame includes two sets of third vertical plates, which are vertically arranged and perpendicular to each other. The intelligent navigation computer module 1 and the power conversion module 2 are respectively arranged on the two sets of third vertical plates.

[0031] The two groups of third vertical panels and the two groups of second vertical panels enclose a rectangular space, and the two groups of first vertical panels are located in the rectangular space.

[0032] In other preferred embodiments, one side of the top plate is provided with an extension plate, the binocular vision module 5 is fixedly connected to the extension plate, and is located on one side of the power supply module 4 .

[0033] In other preferred embodiments, the power supply module 4 is electrically connected to the power conversion module 2 , and the power conversion module 2 is used to power the three-axis fiber optic gyroscope 6 , the intelligent navigation computer module 1 and the three-axis digital accelerometer 3 .

[0034] The power conversion module 2 outputs a voltage of ±5V to match the three-axis fiber optic gyroscope 6 , outputs a voltage of 5V to the three-axis digital accelerometer 3 , and outputs a voltage of 12V to the intelligent navigation computer module 1 .

[0035] In other preferred embodiments, the intelligent navigation computer module 1 is respectively connected to the binocular vision module 5, the three-axis fiber optic gyroscope 6 and the three-axis digital accelerometer 3, and is used to receive and process the output data of the three-axis fiber optic gyroscope 6, the three-axis digital accelerometer 3, the binocular vision module 5 and the dual GNSS module, and output high-precision speed, position, attitude and time information through initial alignment and combined navigation solution.

[0036] In other preferred embodiments, the intelligent navigation computer module 1 adopts a ceramic circuit board with a ZYNQ embedded processor as the core; a dual GNSS module is embedded in the intelligent navigation computer module 1; the dual GNSS module has two antenna interfaces, and the dual antennas are installed on a foldable bracket at the bottom of the intelligent navigation computer module 1 to realize heading measurement; the dual GNSS antenna module is used to receive satellite signals through the antenna and calculate the heading, position, speed, attitude and time information.

[0037] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A portable optical space-time standard measurement system, characterized in that: It includes a base plate, a first frame, a second frame and a third frame. The first frame is arranged in the second frame, and the second frame is arranged in the third frame. A three-axis digital accelerometer is installed in the first frame; a three-axis fiber optic gyroscope is installed on the second frame; an intelligent navigation computer module and a power conversion module are installed on the third frame; a top plate is arranged above the second frame, and a power supply module and a binocular vision module are installed on the top plate.

2. A portable optical space-time standard measurement system according to claim 1, characterized in that: The first frame includes two groups of first vertical plates, which are vertically arranged and perpendicular to each other. The three parts of the three-axis digital accelerometer are respectively arranged on the two first vertical plates and the upper end surface of the bottom plate.

3. The portable optical space-time standard measurement system according to claim 2, characterized in that: The second frame includes two sets of second vertical plates, which are vertically arranged and perpendicular to each other. The three parts of the three-axis fiber optic gyroscope are respectively arranged on the two second vertical plates and the upper end surface of the first frame.

4. The portable optical space-time standard measurement system according to claim 3, characterized in that: The third frame includes two groups of third vertical plates, which are vertically arranged and perpendicular to each other. The intelligent navigation computer module and the power conversion module are respectively arranged on the two groups of third vertical plates.

5. The portable optical space-time standard measurement system according to claim 1, characterized in that: One side of the top plate is provided with an extension plate, and the binocular vision module is fixedly connected to the extension plate and is located on one side of the power supply module.

6. The portable optical space-time standard measurement system according to claim 1, characterized in that: The power supply module is electrically connected to the power conversion module, and the power conversion module is used to supply power to the three-axis fiber optic gyroscope, the intelligent navigation computer module and the three-axis digital accelerometer.

7. The portable optical space-time standard measurement system according to claim 1, characterized in that: The intelligent navigation computer module is connected to the binocular vision module, the three-axis fiber optic gyroscope and the three-axis digital accelerometer respectively, and is used to receive and process the output data of the three-axis fiber optic gyroscope, the three-axis digital accelerometer, the binocular vision module and the dual GNSS module, and output speed, position, attitude and time information through initial alignment and combined navigation solution.

8. The portable optical space-time standard measurement system according to claim 1, characterized in that: The intelligent navigation computer module adopts a ceramic circuit board with a ZYNQ embedded processor as the core; the intelligent navigation computer module is embedded with a dual GNSS module; the dual GNSS module has two antenna interfaces.

Images