Title of Paper:A Backstepping-Based Guidance Law for an Exoatmospheric Missile with Impact Angle Constraint

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Affiliation of Author(s):自动化学院

Journal:IEEE Trans. Aerosp. Electron. Syst.

Abstract:A novel method of exoatmospheric guidance law design is proposed in this paper. By analyzing the nonlinear kinematic equations, a class of nominal motions that requires no maneuver effort can be derived for a nose jet control missile. A unique time to go can be solved online from the equations derived from the property of the nominal motion to guarantee a perfect interception. With the time to go determined, the nominal heading angle and heading angular rate can be obtained to impose an impact angle constraint. A backstepping-based continuous three-order finite-time guidance law is designed such that the heading angle tracking is guaranteed. The superiority of the guidance law is demonstrated by a series of simulation results. © 1965-2011 IEEE.

ISSN No.:0018-9251

Translation or Not:no

Date of Publication:2019-04-01

Co-author:Ye, Qing,lcs,Sun, Jingliang

Correspondence Author:Ye, Qing,guanyeqing