Inertial Navigation/Satellite Integrated Positioning System, that is, the system includes satellite positioning system (GPS (Global Positioning System)/Beidou Satellite Navigation System/GNSS (Global Navigation Satellite System)) and Inertial Orientation Positioning and Navigation System (INS) Orientation positioning and navigation system. According to the complementary characteristics of the INS and satellite navigation functions, the two are combined in an appropriate way to improve the overall navigation accuracy and navigation performance of the system, as well as the ability of air alignment and realignment.
The satellite positioning and navigation system has the characteristics of high precision and communication, but the system cannot provide navigation parameters such as the attitude of the carrier, and when it is used on a flight carrier, due to the maneuvering motion of the carrier, it is often difficult for the receiver to capture and track the satellite's position. The carrier signal even loses lock to the tracked signal; while the inertial orientation positioning and navigation system obtains the current position information through the internal inertial devices (gyroscope, accelerometer), which is airtight and does not need to communicate with the outside world, so it is independent The disadvantage is that as the navigation continues, the inertial navigation will deviate (caused by temperature changes and vibrations, and the deviation can be compensated by the algorithm).
In order to overcome the above shortcomings, according to the complementary characteristics of the navigation functions of INS and GPS, the two are combined in an appropriate way to improve the overall navigation accuracy and navigation performance of the system, as well as the ability of air alignment and realignment. With the aid of inertial navigation position and velocity information, the GPS receiver will also improve the ability of acquisition, tracking and reacquisition, and the navigation accuracy will not decrease too much in the case of poor satellite distribution conditions or few visible satellites. Due to its obvious advantages, GPS/INS combined system is unanimously considered to be the most ideal integrated navigation system for flight vehicles.
In the integrated positioning and navigation system, the inertial system can be corrected regularly through the information of the satellite positioning system. At the same time, when the satellite signal cannot be received, the inertial orientation positioning and navigation system can also ensure the accuracy of the navigation information within a certain period of time.
