Integrated Missile Guidance and Control Scheme via Coupling Effect Utilization and Transformation Mechanism

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Abstract
This paper investigates the usage of the coupling effect between the guidance and control systems of the missile, and proposes an integrated guidance and control law for missile interception. The main feature lies in that not only the couplings beneficial to system convergence are utilized, but also the detrimental ones are conversed and utilized through the defined coupling effect indicator. On this basis, the response rapidity and robustness of interception are improved. Subsequently, the missile interception efficiency is studied under the proposed control strategy, which realizes the interception under external disturbances as well as the unknown target maneuvering with the aid of adaptive disturbance observer enhancing the robustness. By a stability analysis we show that the error states of the closed-loop system are uniformly ultimately bounded. Comparison simulations between the proposed control method and conventional backstepping method on the missile system are performed to validate the effectiveness of the proposed control strategy, and Monte-Carlo campaign is further carried out to verify the robustness.
Funding Information
  • National Natural Science Foundation of China (52272404, 92271109, 52472419)

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