Abstract
This paper investigates the terminal guidance problem for the missile intercepting a maneuvering target with impact time constraint. An impact time guidance law based on finite time convergence control theory is developed regarding the target motion as an unknown disturbance. To further improve the performance of the guidance law, an autopilot dynamics which is considered as a first-order lag is taken into consideration. In the proposed method, the coefficients change with the relative distance between missile and target. This variable coefficient strategy ensures that the missile impacts the target at the desired time with little final miss distance. Then it is proved that states of the guidance system converge to sliding mode in finite time under the proposed guidance law. Numerical simulations are presented to demonstrate the effectiveness of the impact time guidance law with autopilot dynamics (ITGAD).
Highlights
When missiles attack the target with defense system or strong maneuverability, an effective way is salvo attack
We proposed an impact time guidance law for attacking a maneuvering target, in which the impact time and the light-of-sight (LOS) angular rate are chosen as the sliding variables while the motion of target is taken as disturbance
To impact a maneuvering target at a desired impact time, an impact time guidance law based on finite time convergence control theory has been designed
Summary
When missiles attack the target with defense system or strong maneuverability, an effective way is salvo attack. Qu and Zhou [15] presented a dimension reduction observer-based guidance law based on the dynamic surface control-method regarding the missile autopilot as second-order dynamics Taking both the autopilot dynamics and uncertainties into consideration, Li et al [16] developed a finite time convergent guidance law for homing missile to intercept a maneuvering target. To the best of our knowledge, we find that the existing impact time control guidance laws are mainly for hitting the stationary or weak maneuverability target Based on this observation, we proposed an impact time guidance law for attacking a maneuvering target, in which the impact time and the light-of-sight (LOS) angular rate are chosen as the sliding variables while the motion of target is taken as disturbance. Simulation results and analysis of the guidance law are provided
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