Switched bias proportional navigation for homing guidance against highly maneuvering targets

Abstract

A new form of the Proportional Navigation (PN) guidance law for short-range homing missiles is proposed. Named the Switched Bias Proportional Navigation (SBPN) law, it is derived by invoking sliding-mode control theory and is structured around the basic PN, with an additive switched bias term. This additional term depends only on the polarity of the line-of-sight rate, which is readily available with a seeker. It is shown that the bias term acts as an estimate of the target acceleration and other unmodeled dynamics. An adaptive procedure is suggested to select the gain of this term, which results in improved performance. The SBPN is almost as simple to implement as the PN law itself, as it does not require any additional information related to the engagement, in the form of either measurements or estimates. Simulation results show that the acceleration profiles of SBPN closely follow those of augmented PN guidance law, after a short initial transient. They further demonstrate the robustness of the proposed SBPN in the presence of missile velocity variation.

Proportional navigation guidance using predictive and time delay control

“…Although the classical proportional navigation guidance (PNG) is one of the most widely proposed strategies in the homing phase, there exist situations such as the maneuvering target scenario where the simple PNG may not offer satisfactory performance (Lin, 1991). This fact has given rise to various variants of PNG such as the augmented proportional navigation (Nesline & Zarchan, 1981), modified proportional navigation (Ha, Hur, Ko, & Song, 1990), switched bias proportional navigation (Babu, Sarma, & Swamy, 1994) and proportional navigation based on predictive control (Talole & Banavar, 1998) as well as many optimal guidance laws (Asher & Matuszewski, 1974;Speyer, 1976;Salmond, 1996;Zarchan, 1997) which are derived by employing the optimal control theory. Formulation based on the well-known feedback linearization approach (Bezick, Rusnak, & Grey, 1995) is another example of advanced guidance strategy proposed for tactical missiles engaging maneuvering targets.…”

Development and testing of the intercept primitives for planar UAV engagement

“…[18] presented analysis of true PN (TPN) guidance against a maneuvering target. On the other hand, modern guidance laws are developed based on optimal control [19], [11], sliding mode control [20], differential geometry [21], and so on. Interestingly, in a linearized engagement geometry against a moving but non-maneuvering target, TPN was shown to be optimal in [22].…”

A Hybrid Guidance Law for a Strapdown Seeker to Maintain Lock-on Conditions against High Speed Targets

“…The sliding mode control methodology is used in the second phase guidance law derivation [12,13]. In order to apply the sliding mode control, we set a switching surface.…”