A method of in-flight fine alignment for SINS aided by Doppler velocity radar

被引：0
|
作者：
Yang B. [1 ]
Yang X. [1 ]
Xi J. [1 ]
Liu Y. [2 ]
机构：
[1] School of Missile Engineering, Rocket Force University of Engineering, Xi'an
[2] 4th Military Representative Office of Rocket Force Equipment Department in Chengdu Area, Chengdu
来源：
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | 2020年 / 28卷 / 06期
关键词：
Doppler velocity radar; Equivalent velocity; In-flight fine alignment; Installation error of radar; Kalman filter;
D O I：
10.13695/j.cnki.12-1222/o3.2020.06.007
中图分类号：
学科分类号：
摘要：
In order to improve the rapid response capability of aircraft, a method of in-flight fine alignment for SINS with the help of Doppler velocity radar during the flight course of aircraft is proposed. The calibration coefficient error and installation error of Doppler velocity radar are analyzed and modeled, and system state of fine alignment is selected by the error models of SINS and Doppler velocity radar. The equivalent velocity output of radar in navigation coordinate system is obtained by using the attitude output of SINS and the velocity output of Doppler radar. The difference between the equivalent velocity output and the velocity output of SINS is used as the measurement of fine alignment. Then the relationship between the measurement of fine alignment and the system state is derived, and the measurement equation of fine alignment is established. Kalman filter is adopted to design the in-flight fine alignment filtering algorithm. A variety of flight trajectories are designed and generated in the simulation experiment. Simulation results showed that, the accuracy of azimuth aligning is better than 1.4 ' in the process of aircraft motion, and the accuracy of horizontal aligning reached 0.3 '. With the help of the azimuth maneuver, the alignment time is greatly shortened and the azimuth aligning accuracy is significantly improved. The accuracy of azimuth aligning is better than 0.3 ', and the estimation error of azimuth misalignment angle converged rapidly from the beginning of azimuth maneuver. © 2020, Editorial Department of Journal of Chinese Inertial Technology. All right reserved.
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页码：742 / 747
页数：5
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