机载主子惯导间失准角估计的差分惯性滤波器设计及性能分析

doi:10.7527/S1000-6893.2013.0219

Abstract

Abstract:

In order to estimate the mounting misalignments and the flexure angles between a master inertial navigation system (MINS) and slave inertial navigation system (SINS) in the course of flying so as to align airborne mission sensor/weapon systems with high accuracy and monitor the flight state continuously, a scheme for the estimation of misalignment angles between the MINS and SINS based on a differential inertial filter is presented. First, the filter design is introduced involving state and observation equations. Then simulation and performance analysis of the differential inertial filter are accomplished by using representative flexure data and vibration environment data in the references as well as inertial sensor data. The simulation result indicates that using aviation standard inertial navigation system (INS) as MINS and 1-60 (°)/h gyro drift grade INS as SINS, the estimation error of misalignment comes to (0.6-1.5)×10^-3 rad and the alignment converges quickly. These search result provides a technical realization for the development of high accuracy attitude reference and the continuous real-time monitoring of flight status.

Key words: inertial navigation systems, alignment, Kalman filtering, deformation, differential inertial filter

CLC Number:

V241.62⁺2

YUE Yazhou, LI Sihai, ZHANG Yachong, LIU Zhenbo, WANG Jue. Differential Inertial Filter Design and Performance Analysis for Estimation of Misalignment Angle Between Airborne Master INS and Slave INS[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(10): 2402-2410.

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Differential Inertial Filter Design and Performance Analysis for Estimation of Misalignment Angle Between Airborne Master INS and Slave INS

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