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A Calibration Method for Inertial Measurement Unit Applicable to Shaking Base Environment

A technology of inertial measurement unit and calibration method, which is applied in the direction of measuring devices, instruments, etc., can solve the problems of restricting the application of calibration technology and the difficulty of avoiding carrier shaking

Active Publication Date: 2022-02-01
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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Problems solved by technology

[0004] The currently widely used IMU calibration method needs to be applied in a static base environment, that is, during the entire calibration process, the IMU is in a static state except for flipping, but in actual working conditions, it is difficult to avoid Carrier shaking caused by engine vibration, personnel walking or natural environment (strong wind, surge, etc.), thus greatly limiting the application of calibration technology

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  • A Calibration Method for Inertial Measurement Unit Applicable to Shaking Base Environment
  • A Calibration Method for Inertial Measurement Unit Applicable to Shaking Base Environment
  • A Calibration Method for Inertial Measurement Unit Applicable to Shaking Base Environment

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Embodiment Construction

[0046] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0047] see figure 1 As shown, an IMU calibration method suitable for a shaking base environment provided by an embodiment of the present invention includes the following steps:

[0048] S1: Rotate the inertial measurement unit at a set angle sequentially along the axial direction of the inertial measurement unit, and between two adjacent rotations, the inertial measurement unit stands still for a set time, and collects the data output by the inertial measurement unit during the entire rotation process.

[0049] In the embodiment of the present invention, the inertial measurement unit is rotated to set the angle sequentially along the axial direction of the inertial measurement unit, and between two adjacent rotations, the inertial measurement unit is statically set for the time, and the specific steps include:

[0050] Install the inertial me...

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Abstract

The invention discloses an inertial measurement unit calibration method suitable for a swaying base environment, and relates to the technical field of inertial measurement combined testing in aerospace strapdown inertial navigation technology. Based on the established simultaneous equations, solve the first-order error parameters; use the first-order error parameters to calculate the second-order intermediate parameters of the i-th position, according to the relationship between the second-order intermediate parameters and the second-order error parameters Establishing an equation based on the relationship between the equations, solving to obtain a second-order error parameter, the second-order error parameter being the gyroscope zero bias; judging whether the residual error of the first-order error parameter and the second-order error parameter is less than the set threshold, and if so, then ending. The invention adopts an iterative method to gradually eliminate the attitude error introduced by the shaking base environment during the initial alignment process, so that it is better suitable for calibration in the shaking base environment.

Description

technical field [0001] The invention relates to the technical field of inertial measurement combined testing in aerospace strapdown inertial navigation technology, in particular to an inertial measurement unit calibration method suitable for a shaking base environment. Background technique [0002] The inertial navigation system can provide completely autonomous navigation information, and has the advantages of short response time, high reliability, small size, and light weight. It is widely used in military and civilian navigation fields such as aircraft and ships, and has important national defense significance and huge economic benefits. However, during the use of the inertial navigation system, its errors will continue to accumulate over time. Currently, two measures can improve the navigation accuracy of the inertial navigation system: one is to design and manufacture higher-precision inertial components, such as using new materials , new technology or new inertial dev...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 穆杰刘明王勇胡华峰李旦
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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