3D Guidance Law against Maneuvering Target with Time and Angle Constraints

A terminal guidance law with time and angle constraints is proposed for the scenario of multiple missiles collaborating to attack a maneuvering target in the three-dimensional space. After the relative motion equations of missile and target are established, a guidance law based on nonsingular predefined time convergence sliding mode surface is designed in the vertical line-of-sight direction, which can make the line-of-sight angle error converge within a predefined time. And an optimal guidance law is designed along the line-of-sight direction, which allows the missile to attack the target at the expected time. The numerical simulation results demonstrate the significance of the method proposed by us.