Abstract
It is known from the previous chapters that strapdown inertial navigation system (SINS)/global navigation satellite system (GNSS) integrated navigation corrects the velocity and position errors of SINS online by using high-precision velocity and position information measured by GNSS to realize the longtime and high-precision positioning and navigation, but it is hard to estimate the attitude error rapidly and accurately, and the GNSS signal is susceptible to external interference. The SINS/celestial navigation system (CNS) integrated navigation corrects attitude error and gyro drift online by using high-precision attitude information measured by CNS and can effectively correct position error of the launching point, which is of great significance for the mobile launching of missile, but it is unable to completely inhibit divergence of velocity and position errors of SINS, and CNS is restricted by climate conditions. Therefore, the combination of SINS, CNS, and GNSS that effectively constitute the SINS/CNS/GNSS integrated navigation system can realize the correction of velocity error, position error, and attitude error of SINS simultaneously. At present, the SINS/CNS/GNSS integrated navigation system has become the most effective way for high-performance navigation of medium and long-range ballistic missile and high-altitude long-endurance flying machine, etc.
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