Finite-Time Guidance Laws for Three-Dimensional Missile-Target Interception Problem

In this paper, relative kinematic equations of three-dimensional missile-target interception problem are presented in the form of three connected double integrator subsystems subjected to unknown target acceleration. By applying a new class of terminal sliding mode control approach, three guidance laws, which are components of missile acceleration, are designed to precisely steer the missile to the target in an adjustable finite time. The obtained relation for determining the mentioned finite time shows that it depends on several arbitrary parameters and, in consequence, the finite time is adjusted by tuning these parameters. Finally, a numerical simulation is provided to verify the effectiveness of the proposed finite-time guidance laws.

کلیدواژه ها:

Missile-target interception ، finite-time guidance laws ، terminal sliding mode control ، finite-time stabilization