High-precision initial alignment method of ship strapdown inertial navigation system
An initial alignment and strapdown inertial navigation technology, applied in the field of inertial navigation, can solve problems such as slow alignment time, inability to play inertial device performance, and inability to achieve optimal alignment performance, and achieve the effect of improving alignment accuracy
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
Embodiment 1
[0010] A high-precision initial alignment method for ship strapdown inertial navigation system, see figure 1 , the method includes: based on the error propagation law of the ship SINS and the precise position and speed reference provided by the external high-precision positioning equipment, the initial alignment model of the ship SINS is established; based on the Kalman The filtering method estimates the initial alignment model, wherein, by adjusting the dimension of the system state covariance matrix, optimizing the system state covariance matrix, a part of the error amount of the initial alignment model is preferentially iteratively estimated; On the basis of prioritizing the estimation of a part of the error amount, iteratively estimate the remaining error amount of the initial alignment model; wherein, in the process of iterative estimation, the system state covariance is optimized by adjusting the size of the system state covariance matrix matrix.
[0011] Among them, th...
Embodiment 2
[0014] A high-precision initial alignment method for a ship's strapdown inertial navigation system, the method mainly includes the following steps:
[0015] S1. Based on the propagation law of various error quantities of the ship SINS and the precise position and velocity reference provided by the external high-precision positioning equipment, the initial alignment model of the ship SINS is established.
[0016] Specifically, the establishment of the initial alignment model according to the inertial navigation error propagation law and the technical state of the inertial navigation equipment itself can be expressed as:
[0017]
[0018] in, is the east, north, azimuth and attitude angle error, δV E , δV N , δV U is the eastward, northward and skyward speed error, δL and δλ are latitude and longitude errors, ε x , ε y , ε z is the gyro drift, is the accelerometer zero bias, and
[0019] Its state equation can be expressed as:
[0020]
[0021] Wherein, the ob...
PUM
Login to View More Abstract
Description
Claims
Application Information
Login to View More 


