METHOD FOR CORRECTING THE ORIENTATION ANGLES OF PLATFORMLESS INS ON A SLIDING INTERVAL Russian patent published in 2023 - IPC G01C21/06 

FIELD: measuring technology.

SUBSTANCE: invention relates to measuring technology and can be used for sea, air and land objects. The objective of the invention is to increase the accuracy of a platformless inertial navigation system (PINS) by creating a method for continuous correction of orientation angles from a satellite navigation system (SNS) with one receiver, ensuring the universality of its use for any aircraft. A method for correcting the orientation angles of the PINS on a sliding interval, in which the roll and pitch angles of the aircraft are determined by the signals of the angular velocity sensors (AVS) and the roll and pitch angles of the PINS are corrected by joint processing of angular velocities, linear accelerations of the aircraft. At the same time, the current course of the aircraft is additionally corrected using the projections of ground velocities obtained from one SNS receiver, for this purpose, multiple measurements are used together on a sliding observation interval, three arrays of satellite velocities, three arrays of angular velocities and three arrays of linear accelerations are of the same dimension. Next, the presence of angular velocities of rotation of the aircraft and their variability in the considered interval are determined. At the same time, algorithms are proposed for the joint assessment of the roll, pitch and course of the aircraft by measurements of three-component sensors of the AVS, linear acceleration sensors and one receiver of the SNS by an iterative algorithm using the Hartley method. This algorithm is convenient for practical application, as it can be implemented with relatively small computational costs. To apply the algorithm in question, its pre-configuration on processes specific to a particular type of aircraft is not required.

EFFECT: increase in accuracy and ensuring continuous correction of pitch, roll and course angles in flight maneuvering conditions.

1 cl, 5 dwg