Algorithmic Computation of Strapdown Inertial Navigation Parameters: Velocity, Latitude/Longitude, and Attitude Angles

This section elaborates on the computational process of strapdown inertial navigation systems (SINS). SINS represents a high-precision navigation technology utilizing three gyroscopes and three accelerometers to measure aircraft motion. Through integration algorithms applied to gyroscope and accelerometer measurements, we derive critical parameters including aircraft position, velocity, and attitude angles. These parameters are essential for navigation and control systems, particularly in GPS-denied or GPS-unstable environments. Consequently, SINS has become an indispensable component in modern aircraft. During parameter computation, multiple factors must be addressed through algorithmic implementations: attitude angle transformations using direction cosine matrices or quaternion methods, accelerometer error compensation through calibration routines, and gyroscope drift correction using kalman filtering techniques. Only through comprehensive consideration of these factors in the algorithmic design can accurate and reliable computational results be achieved.