Miniaturized micro-electro-mechanical gyro inertia/satellite integrated navigation system

Abstract

The invention discloses a miniaturized micro-electro-mechanical gyro inertia / satellite integrated navigation system, and the system is composed of a top cover, a base, an integrated navigation measurement unit, a power supply connector and a satellite receiver radio frequency connector. The base is connected with the top cover and the integrated navigation measurement unit through screws, providessupport for the top cover and the integrated navigation measurement unit, and has installation references in three directions of pitching, rolling and orientation; the integrated navigation measuringunit is composed of an inertia measuring circuit, a satellite receiver circuit and a supporting structure. The inertial measurement circuit and the satellite receiver circuit are installed on the same supporting structure, and the inertial measurement circuit is composed of an information processor, three gyroscopes and three accelerometers. According to the scheme, the inertial measurement circuit and the satellite receiver circuit of the micro-electro-mechanical gyro inertial / satellite integrated navigation system are installed on one structural body, so the installation surface is reduced,the structure is simplified, and the size is smaller.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation used in aircraft and vehicles, and in particular relates to a micro-electromechanical gyro inertial / satellite integrated navigation system for inertial measurement and integrated navigation. Background technique [0002] Inertial / satellite integrated navigation measures the acceleration and angular rate movement of the carrier through inertial instruments (including accelerometers and gyroscopes), and obtains the acceleration, angular rate, attitude, position and speed of the measured carrier through error compensation and integration. At the same time, the carrier position, velocity and other information measured by the satellite navigation module are used for data fusion to form continuous high-precision inertial / satellite combination position, velocity, attitude and other information. Due to the advantages of continuous, high precision, non-divergence, etc., it is widely used in the...

AI Technical Summary

Problems solved by technology

Due to the advantages of continuous, high precision, non-divergence, etc., it is widely used in the fields of unmanned vehicles, unmanned aerial vehicles, robot navigation, surveying and mapping imaging load motion error compensation, railway track detection, etc. Among them, MEMS gyro inertial / satellite integrated navigation system It has the advantages of small size, light weight, low power consumption, low cost, and easy mass production. It is required for the volume of inertial measurement and integrated navigation systems in small UAVs, unmanned vehicles, robots, small guided munitions, and integrated surveying and mapping equipment. Higher fields are widely used, but the integration of inertial devices, information processing circuits, and receiver modules in a small volume has problems such as reduced system structural strength, reduced sealing performance, low installation accuracy, and poor heat dissipation, which lead to problems such as micro-electromechanical gyroscopes. The accuracy of the inertial / satellite integrated navigation system decreases, and the environmental adaptability is poor. In view of the above problems, the present invention provides a small volume and high precision MEMS gyro inertial / satellite integrated navigation system solution

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