A Backstepping-Based Guidance Law for an Exoatmospheric Missile with Impact Angle Constraint

Qing Ye; Chunsheng Liu; Jingliang Sun

doi:10.1109/TAES.2018.2852419

A Backstepping-Based Guidance Law for an Exoatmospheric Missile with Impact Angle Constraint

Qing Ye, Chunsheng Liu^*, Jingliang Sun

^*Corresponding author for this work

Nanjing University of Aeronautics and Astronautics

Research output: Contribution to journal › Article › peer-review

17 Citations (Scopus)

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.

Original language	English
Article number	8402114
Pages (from-to)	547-561
Number of pages	15
Journal	IEEE Transactions on Aerospace and Electronic Systems
Volume	55
Issue number	2
DOIs	https://doi.org/10.1109/TAES.2018.2852419
Publication status	Published - Apr 2019
Externally published	Yes

Keywords

Backstepping
exoatmospheric guidance
impact angle constraint

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10.1109/TAES.2018.2852419

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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.",

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AU - Sun, Jingliang

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Y1 - 2019/4

N2 - 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.

AB - 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.

KW - Backstepping

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KW - impact angle constraint

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A Backstepping-Based Guidance Law for an Exoatmospheric Missile with Impact Angle Constraint

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Keywords

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