Research on Sliding Mode Method about Three-Dimensional Integrated Guidance and Control for Air-to-Ground Missile

Wang, Zhikai; Ma, Jianwei; Fu, Jiangtao

doi:10.5028/jatm.v11.982

Cited by 2 publications

(1 citation statement)

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“…The sliding mode control that has the advantages of robustness to system uncertainties and external disturbances has been widely used in the guidance law. [10][11][12][13] Ge et al 11 proposed a head pursuit guidance law for three-dimensional hypervelocity interception by using the sliding mode control to reduce the effect of the perturbation induced by seeker detection. Song et al 12,13 gave a three-dimensional adaptive guidance law and finite-time cooperative guidance law with impact angle constraints for the missile and multiple missiles, respectively, by using the integral sliding mode and terminal sliding mode control.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional impact angles constrained integral sliding mode guidance law for missiles with input saturation

Qian

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes the three-dimensional impact angles constrained integral sliding mode guidance laws for the missile with the constraint of the input saturation. To solve the problem of the input constraint, an integral sliding mode surface is given for the first time by using the saturation function. The first three-dimensional integral sliding mode guidance law can solve the impact angle constraint and the target accelerations with known upper bound, while the second one can solve the impact angle constraint, input saturation, and the target accelerations with unknown upper bound simultaneously. Finally, numerical simulations are used to verify the effectiveness of the guidance laws.

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