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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… Click to show full 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.
Journal Title: IEEE Transactions on Aerospace and Electronic Systems
Year Published: 2019
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