Strapdown Inertial Navigation System Navigation Solution

MATLAB 2K 213 views 0 downloads 1 credits
Tags:

Resource Overview

Strapdown Inertial Navigation System Navigation Solution. Navigation computation using 600 seconds of north-oriented strapdown system data with constant flight altitude and 0.01s sampling period. Implementation involves attitude updating through quaternion integration and position calculation using velocity and acceleration data.

Detailed Documentation

In this paper, we discuss the navigation solution for Strapdown Inertial Navigation Systems (SINS). The SINS calculates aircraft position and orientation by processing north-oriented inertial measurement data. For navigation computation, we utilize strapdown system data with specific parameters. In this study, we employ 600 seconds of north-oriented strapdown system data, performing navigation solutions under constant flight altitude conditions with a 0.01-second sampling period. The implementation typically involves numerical integration algorithms like Runge-Kutta methods for attitude computation and dead reckoning techniques for position updates. Key functions include sensor data preprocessing, coordinate transformation matrices, and navigation state propagation. These datasets are processed to determine aircraft position and orientation, providing fundamental references for future aviation research applications.

You May Also Like