Design of missile guidance law via variable structure control

Abstract

The missile guidance law utilizing variable structure control is proposed. The acceleration command input is determined considering the target acceleration as uncertainty. The target and the missile are assumed to be point masses moving in a twodimensional plane. According to the property of missile acceleration, the proposed guidance law can be classified into the IPN type and the RTPN type. It is also shown that the conventional proportional guidance laws can be derived from the proposed guidance law. To compensate for the effects of the uncertainty in the target acceleration, the perturbed guidance command is introduced. Numerical simulations show that the proposed guidance law yields better performance compared to the conventional proportional guidance laws.

Three dimensional adaptive dynamic surface guidance law accounting for autopilot lag

“…However, the target acceleration is hard to be estimated precisely. Therefore, some robust control algorithms have been applied to guidance problems such as the H  guidance law [5][6][7], the L2 gain guidance law [8], the Lyapunov nonlinear guidance law [9] and the variable structure guidance law [10][11][12][13][14][15].…”

Missile Interceptor Guidance and Control Using Second Order Sliding Modes

“…The important issue here is to design a continuous/smooth control, ) (t n Lc , to be enforced for the actual missile normal acceleration ) (t n L . That's why absolute robustness to uncertainties and finite time convergence are traded for approximation of an ideal discontinuous SMC law by a linear saturation function (see Moon, & Kim, 2000;. In this case the output is robustly regulated to a small domain of convergence around zero.…”

“…Optimal guidance law (OGL) effectively compensates for a single-lag frame dynamics in presence of a step-constant target maneuver modifying APN by using information of time-to-go and effective time-constant of the guidance system. However, OGL is difficult to derive and implement (see Zarchan, 1998).Recent application of sliding mode control (SMC) (see Utkin 1998) to the homing missile guidance (see Brierly and Longchamp, 1990;Babu, Sarma, and Swamy, 1994;Zhou, Mu, and Xu, 1999;Moon and Kim, 2000;, resulted in a series of very effective algorithms in terms of smaller acceleration advantage required for intercept of weaving targets as compared to PN and APN guidance. Though SMC guidance doesn't use direct estimate of target acceleration, it's comparable to OGL.…”

Integrated CLOS and PN Guidance for Increased Effectiveness of Surface to Air Missiles

“…One such research [12] suggests using variable structure control for design of augmented true PN guidance law that makes use of the information of target acceleration bound only. Another research [13] evaluates the performance for a short range homing surface-to-air missile by using PN guidance as the guidance law and Coefficient Diagram Method to design normal acceleration and roll angle control system.…”