Transfer alignment filter, transfer alignment method and guidance aircraft applying transfer alignment filter and transfer alignment method

Abstract

The invention discloses a transfer alignment filter, a transfer alignment method and a guidance aircraft applying the transfer alignment filter and the transfer alignment method. According to the system, an INS inertial element can be assisted to shorten the zero alignment time, errors caused by gyroscopic drift and zero offset of an accelerometer can be compensated at the same time, the sensitiveprecision of the INS inertial element is improved, and the hit precision of the aircraft is further ensured. Particularly, information transmitted by a satellite receiving system and a geomagnetic sensor is processed through a Kalman filter to obtain three-axis acceleration information based on satellites and three-axis angular rate information based on geomagnetism, the information is compared with the information output by the INS inertial element, the difference value is used as a reference correction parameter of the INS inertial element, and the INS inertial element is corrected according to the reference correction parameter, so that the zero alignment time of the INS inertial element is shortened, and the guidance precision of the guidance aircraft is improved.

Description

technical field [0001] The invention relates to a system and method for transferring alignment of sensitive components in a guided aircraft, in particular to a transfer alignment filter, a method and a guided aircraft using the same. Background technique [0002] Traditionally guided aircraft mostly use INS inertial guidance elements for attitude sensitivity. However, the inertial navigation system needs to align the zero reference after it starts to work. It takes a period of time before it can accurately sense the attitude of the aircraft and obtain the three-axis angular rate information and three-axis acceleration information. The characteristics of the guided aircraft determine its The inertial navigation system will not be given enough time for zero alignment, which will affect the sensitive accuracy of attitude measurement, and then cause an irreversible impact on the guidance control and hit accuracy of the aircraft. In the prior art, the time required for zero alig...

AI Technical Summary

Problems solved by technology

However, the inertial navigation system needs to align the zero reference after it starts to work. It takes a period of time before it can accurately sense the attitude of the aircraft and obtain the three-axis angular rate information and three-axis acceleration information. The characteristics of the guided aircraft determine its The inertial navigation system will not be given enough time for zero alignment, which will affect the sensitive accuracy of attitude measurement, and then have an irreversible impact on the guidance control and hit accuracy of the aircraft

In the prior art, the time required for zero alignment of INS inertial guidance components is about 10 to 12 seconds, and the shorter the zero alignment time, the higher the general cost;

[0003] In addition, INS inertial guidance components will produce gyro drift and accelerometer zero bias as the working time prolongs, which makes the attitude measurement at the end of the trajectory of the remote guided aircraft have certain errors, which in turn increases the amount of misses;

[0004] In addition, the three-axis acceleration information can also be obtained by processing the satellite signal, and the three-axis angular rate information can also be obtained by processing the geomagnetic sensor information, but the accuracy of the information obtained through the satellite signal and the geomagnetic sensor is low. The precision of INS inertial guidance components before zero alignment is high, but its accuracy is also lower than that of INS inertial guidance components after zero alignment; so it is not only necessary to ensure that the guidance system can be based on more accurate information during the guidance process For guidance control, it is necessary to shorten the zero alignment time of the INS inertial components as much as possible, so as to further improve the accuracy of guidance control

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