Two robust homing missile guidance laws based on sliding mode control theory

Abstract

Two new guidance laws for short range homing titissiles are developed by invoking the Sliding Mode Control (SMC) theory. Guidance law 1 is structured around the basic Proportional Navigation (PN), with an additive switching term, which is a function of the Line of ,Sight (LOS) rate alone. A n adaptive procedure is suggested to select the gain of the switching term, in order to reduce chattering. This guidance law is nearly as siinple to implement as the P N itself and does not require any explicit target maneuver estimation. Guidance Law 2, based on a first order sliding surface, is designed such that it results in a continuous acceleration law, thereby wducing the chatiering problem. While ezplicitly taking into account the effect of aerodynamic drag, it requires the second derivatives of LOS angle and range, which are not directly weasured. A n estimation scheme, again based on sliding mode theory, is presented to estimate these quantities. Sirnulation results clearly demonstrate the superior performance of these schemes.

Sliding Mode and Inertial Delay Control Based Missile Guidance

“…Letĥ denote an estimate of h which can be obtained by following the procedure for IDC-based estimation of the uncertainty given in [23] aŝ (17) or in the time domain as…”

“…From (8) and (31) and using (17) it can be shown that the last two terms of (34) consist of an estimate of target acceleration. In fact these terms would have given the estimate of target acceleration only had the uncertainty to be estimated (8) been defined in terms of the target acceleration alone.…”

“…For example in [5], a guidance law formulation called SBPN is proposed wherein a bias is added to the basic PNG to compensate for target acceleration. Similarly, in [17] two SMC-based guidance laws using different switching surfaces are presented. More formulations based on the SMC approach can be found in [18]- [22].…”

A novel robust proportional navigation guidance law design for missile considering autopilot dynamic

“…In (Hu et al, 2011), a three-dimensional guidance law has been developed for impact angle control, using the linear quadratic optimal theory and the SMC methodology. Babu et al (1994) developed two guidance laws in twodimensional space for short-range homing missiles by invoking SMC theory and based on PNG. They have also chosen the line-of-sight (LOS) angle rate as the switching surface.…”

“…Babu et al (1994) developed two guidance laws in two-dimensional space for short-range homing missiles by invoking SMC theory and based on PNG. They have also chosen the line-of-sight (LOS) angle rate as the switching surface.…”