This work focuses on the problem of the guidance laws design in the presence of impact angle constraint by using adaptive control and non-singular terminal sliding mode control (NTSMC) with two guidance laws proposed. Utilizing the missile-target relative movement equation in a 2D plane, the first guidance law is finite-time stability, while, the second one with dynamic delay in the missile autopilot is exponential stability. In order to avoid the decreasing of the guidance performance caused by estimating the target maneuvering’s upper bound too high or too low, an online adaptive guidance law is employed to estimate the respective upper bound. These simulations indicate that, from different models of target maneuvering, the missiles with the designed guidance laws could hit the targets from an expected line-of-sight angle.
Adaptive Sliding Mode Guidance Law with Impact Angle Constraint
Lect. Notes Electrical Eng.
2021-10-30
16 pages
Article/Chapter (Book)
Electronic Resource
English
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