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.
A Backstepping-Based Guidance Law for an Exoatmospheric Missile With Impact Angle Constraint
IEEE Transactions on Aerospace and Electronic Systems ; 55 , 2 ; 547-561
2019-04-01
1657644 byte
Article (Journal)
Electronic Resource
English
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