Aerial in-flight alignment method for SINS/GPS combined navigation system

A technology of integrated navigation system and GPS antenna, which is applied in the field of air maneuver alignment of SINS/GPS integrated navigation system, which can solve the problems of decreased system accuracy, no improvement of navigation system accuracy, system divergence, etc., and achieve the effect of improving accuracy
CN1763475AInactive Publication Date: 2006-04-26BEIHANG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
BEIHANG UNIV
Publication Date
2006-04-26
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention discloses an aerial motor alignment method of SINS / GPS combination navigation system, which is characterized by the following: supplementing the lever effect error of GPS observed quantity, which improves the precision of observed quantity; adapting the motor strategy of course variation; utilizing the singular value decomposition method to analyze each system observed degree variation of status variable; adapting the adaptive feedback strategy; adjusting feedback factor of system status variable according to the variation of observed degree; correcting the feedback factor. The invention is fit for the navigation precision improvement such as plane, missile and ship or vehicle combination navigation system.
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Description

technical field

[0001] The invention relates to an air maneuver alignment method of a SINS / GPS integrated navigation system, which can be used to improve the navigation accuracy of the SINS / GPS integrated navigation system used for aircraft, missiles, ships or ground vehicles. Background technique

[0002] Strapdown Inertial Navigation System (SINS) is a completely autonomous navigation system that can provide position, velocity and attitude information continuously and in real time. It has high short-term accuracy, good concealment, and is not limited by weather conditions. , and thus widely used in aviation, aerospace, navigation and other fields. However, the SINS error increases with time, so it is often combined with the GPS global satellite positioning system to form a SINS / GPS integrated navigation system. In the SINS / GPS integrated navigation system, GPS can provide position and velocity information, but cannot provide attitude information. Since the position error ...

Claims

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