Designing a new and better terminal guidance law based on Nussbaum-type gain technique

Aim. The introduction of the full paper reviews Refs. 1 through 9 and then proposes the design of what we believe to be a new and better terminal guidance law. Sections 1 and 2 explain our design; their core consists of: (1) we build the mathematical model for three-dimensional interception according to the relative motion relationship between the interception missile and its target; (2) we employ the Nussbaum-type gain technique and the idea of zeroing the rate of line-of-sight angle to design the continuous nonlinear terminal guidance law; (3) we prove the stability of the terminal guidance system by using the Lyapunov stability theory and attempt to zero the product ab, where a is the line-of-sight rate and b is the relative distance between the missile and its target within the limited time. Section 3 simulates our terminal guidance law; the simulation results, presented in Figs. 2 through 4 and Table 1, and their analysis show preliminarily that our new and better terminal guidance law is indeed more robust and suitable for the missile that intercepts the target of high velocity and high maneuver than the conventional optimal proportional navigation law and that our terminal guidance law is of better precision.