An Air Alignment Method for the Roll Angle of Rolling Missiles with Velocity Matching and Maneuvering Assistance

doi:10.3969/j.issn.1000-1093.2019.07.008

Abstract

Abstract: A method of satellite/inertial velocity matching and maneuvering assistance is proposed to solve the problem of low accuracy of aligning the roll angle by a satellite/inertial velocity matching method. In the satellite/inertial integrated guidance mode, on the basis of observability analysis, a longitudinal proportional guidance law with gravity compensation is used in the maneuvering assistance, and Kalman filter is used to complete the air alignment of roll angle. The influences of maneuvering assistance strategy on the aligning effect of roll angle are analyzed in the case of different navigation ratios and gravity compensation coefficients, and the influences of nominal rotating speed deviation and inertial system error deviation on maneuvering assistance strategy are also analyzed. Simulated results show that the proposed method can be used to realize the precision alignment of roll angle in the whole trajectory with the error of less than 2° and the convergence time of 10 s under the condition of satellite and inertial system errors, and the speed and precision of alignment can be changed by adjusting the gravity compensation coefficient. The navigation ratio is used to ensure the stability of guidance loop. Moreover, under the condition that the deviations exist in the nominal rotating speed and the inertial system errors, the alignment effect is less affected and the anti-interference ability is stronger. Key

Key words: rollingmissile, velocitymatching, maneuveringassistance, Kalmanfiltering, rollangle, airalignment

CLC Number:

V249.32⁺8

PENG Bo, CEN Mengxi. An Air Alignment Method for the Roll Angle of Rolling Missiles with Velocity Matching and Maneuvering Assistance[J]. Acta Armamentarii, 2019, 40(7): 1390-1400.

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第40卷
第7期2019 年7月兵工学报ACTA
ARMAMENTARIIVol.40No.7Jul.2019

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